LOAN copy: retlpn to
AFWL TECHNICAL U'^^nA^rf
KIRTLAND AFB, N. •
HEAT TRANSFER TO A FULL-COVERAGE
FILM-COOLED SURFACE WITH 30 ^
SLANT-HOLE INJECTION
Af. E. Crawford, W. M. Kays,
and R. J, Moffat
Prepared by
STANFORD UNIVERSITY
Stanford, Calif. 94305
for Lewis Research Center
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION • WASHINGTON, D. C. • DECEMBER 1976
1. Report No. 2. Government Accession No.
NASA CR-2786
4. Title and Subtitle
HEAT TRANSFER TO A FULL-COVERAGE FILM -COOLED
SURFACE WITH 30® SLANT -HOLE INJECTION
TECH LIBRARY KAFB. NM
□□b3i3t>a
5. Report Date
6. Performing Organization Code
7. Author(s)
M. E. Crawford, W. M. Kays, and R. J. Moffat
9. Performing Organization Name and Address
Stanford University
Stanford, California 94305
8. Performing Organization Report No.
HMT-25
10. Work Unit No.
11. Contract or Grant No.
NAS3-14336
13. Type of Report and Period Covered
Contractor Report
14. Sponsoring Agency Code
12. Sponsoring Agency Name and Address Contractor Report
National Aeronautics and Space Administration ^ —
^ 14. Sponsoring Agency Code
Washington, D.C. 20546
15. Supplementary Notes
Final Report. Project Manager, Raymond S. Colladay, Fluid System Components Division,
NASA Lewis Research Center, Cleveland, Ohio
1 6. Abstract
Heat transfer behavior was studied in a turbulent boundary layer with full-coverage film cooling
through an array of discrete holes and with injection 30® to the wall surface in the downstream
direction. Stanton numbers were measured for a staggered hole pattern with pitch-to-diameter
ratios of 5 and 10, an injection mass flux ratio range of 0. 1 to 1. 3, and a range of Reynolds num-
ber Re^ of 1. 5X10^ to 5x10°. Air was used as the working fluid, and the mainstream velocity
varied from 9.8 to 34. 2 m/sec (32 to 112 ft/sec). The data were taken for secondary injection
temperatures equal to the wall temperature and also equal to the mainstream temperature. The
data may be used to obtain Stanton number as a continuous function of tiie injectant temperature
by use of linear superposition theory. The heat transfer coefficient is defined on the basis of a
mainstream -to -wall temperature difference. This definition permits direct comparison of per-
formance between film cooling and transpiration cooling. A differential prediction method was
developed to predict the film cooling data base. The method utilizes a two-dimensional boundary
layer program with routines to model the injection process and turbulence augmentation. The
program marches in the streamwise direction, and when a row of holes is encountered, it stops
and injects fluid into the boundary layer. The turbulence level is modeled by algebraically
augmenting the mixing length, with the augmentation keyed to a penetration distance for the in-
jected fluid. Most of the five -hole diameter data were successfully predicted.
17. Key Words (Suggested by Author(s))
Boundary layer
Film cooling
Heat transfer
Turbulence
19. Security Classif. (of this report)
Unclassified
18. Distribution Statement
Unclassified - unlimited
STAR category 34
20. Security Classif. (of this page)
Unclassified
21. No. of Pages
245
22. Price*
$ 8.00
For sale by the National Technical Information Service, Springfield, Virginia 22161
Table of Contents
Page
Chapter 1. INTRODUCTION 1
1.1 Background for the Problem 1
1.2 Full-Coverage Film Cooling 2
1.3 Heat Transfer with Film Cooling 5
1.4 Literature Review 7
1.4.1 Experimental Works 7
1.4.2 Analytical Works 9
1.5 Objectives for the Present Research 11
Chapter 2. EXPERIMENTAL FACILITY AND METHODOLOGY 13
2.1 Discrete Hole Rig 13
2.1.1 Primary Air Supply System 13
2.1.2 Secondary Air Supply System 14
2.1.3 Test Plate Electrical Power System 14
2.1.4 Preplate/Af terplate Heating System 14
2.1.5 Heat Exchanger Cooling Water System 15
2.2 The Test Surface 15
2.2.1 Discrete Hole Test Section 15
2.2.2 Preplate and Afterplate 16
2.3 Rig Instrumentation and Measurement 17
2.3.1 Temperature 17
2.3.2 Pressure 18
2.3.3 Test Plate Power 18
2.3.4 Afterplate Heat Flux 18
2.3.5 Secondary Air Flow Rate . 18
2.3.6 Velocity and Temperature Profiles ....... 19
2.4 Formulation of the Heat Transfer Data . 19
2.4.1 Radiation Loss 20
2.4.2 Conduction Loss 21
2.4.3 Secondary Air Exit Temperature 22
2.4.4 Convection Between Plate and Secondary Air . • 23
2.4.5 Energy Balance Closure 24
ill
Page
2,5 Rig Qualification 2,6
2.5.1 Hydrodynamics . 26
2.5.2 Heat Transfer ....,, 27
Chapter 3. EXPERIMENTAL DATA 34
3.1 Types of Data 34
3.2 Description of the Stanton Number Data ....... 34
3.3 Stanton Number Data 37
3.3.1 Thick Initial Boundary Layer with Heated
Starting Length 38
3.3.2 Thick Initial Boundary Layer with Unheated
Starting Length 40
3.3.3 Thick Initial Boundary Layer with Change in
Mainstream Velocity 43
3.3.4 Thin Initial Boundary Layer with Heated
Starting Length 45
3.4 Spanwise Velocity and Temperature Profiles 47
Chapter 4. ANALYSIS OF THE DATA 78
4.1 Effects of Full-Coverage Film Cooling on Stanton
Number 78
4.1.1 Inject ant Temperature and Blowing Ratio ... 78
4.1.2 Upstream Initial Conditions 80
4.1.3 Hole Spacing 81
4.2 Correlation of the Stanton Number Data . 81
4.3 Development of a Prediction Model 83
4.3.1 Injection Model . 85
4.3.2 Turbulence-Augmentation Model 89
4.4 Numerical Prediction of the Data 93
iv
Page
Chapter 5. SUMMARY AND RECOMMENDATIONS 109
Appendix I. STANTON NUMBER DATA 112
II. SPANWISE PROFILE DATA 181
III. STANTON NUMBER DATA REDUCTION PROGRAM 206
IV. ON THE HEAT TRANSFER BEHAVIOR FOR THE INITIAL
FILM-COOLING ROWS 223
V. ON AN ASYMPTOTIC STANTON NUMBER AND JET
COALESCENCE 226
VI. SHEAR STRESS AND MIXING-LENGTH PROFILES 228
References 230
V
List of Figures
Figure Page
1.1 Full-coverage film-cooled turbine blade and blade cavity . 2
1.2 Hole-pattern and heat transfer area for slant-hole in-
jection test surface 4
2.1 Flow schematic of wind tunnel facility, the Discrete Hole
Rig 29
2.2 Photograph of Discrete Hole Rig 30
2.3 Photograph of slant-hole injection test surface, showing
staggered hole array 30
2.4 Cross-sectional drawing of the discrete hole test sec-
tion 31
2.5 Close-up photograph of discrete hole test surface .... 32
2.6 Photograph of test section cavity showing secondary air
delivery tubes 32
2.7 Configurations for tunnel topwall and boundary layer trip:
//I is for thick initial boundary layer; #2 is for thin
initial boundary layer 33
3.1 Upstream velocity profile for initially high ^^62 *
heated starting length runs (see Section 3.3.1) 50
3.2 Upstream temperature profile for initially high Red 2 »
heated starting length runs (see Section 3.3.1) 51
3.3 Stanton number data versus non-dimensional distance along
surface for initial conditions in Figures 3.1 and 3.2, to
study effects of heated starting length . 52
3.4 Data from Figure 3.3, replotted versus enthalpy thickness
Reynolds number 53
3.5 Upstream velocity profiles (P/D = 5, 10) for initially
high Re^^ , unheated starting length runs (see Section
3.3.2) .7 54
3.6 Stanton number data (P/D = 5) versus non-dimensional dis-
tance along surface for Initial conditions in Figure 3.5,
to study effects of blowing ratio 55
vi
Figure Page
3.7 0=1 data from Figure 3.6, replotted versus enthalpy
thickness Reynolds number •
3.8 6=0 data from Figure 3.6, replotted versus enthalpy
thickness Reynolds number 57
3.9 Stanton number data (P/D = 10) versus non-dimensional 4is-
tance along surface for initial conditions in Figure 3.5,
to study effects of change in hole spacing 58
3.10 Data from Figure 3.9, replotted versus enthalpy thickness
Reynolds number 59
3.11 Upstream velocity profile for initially high
heated starting length runs (see Section 3.3.3) . 60
3.12 Stanton number data versus non-dimensional distance along
surface for initial conditions in Figure 3.11, to study
effects of change in 61
3.13 Data from Figure 3.12, replotted versus enthalpy thickness
Reynolds number .......... 62
3.14 Upstream velocity profile for initially high ^©62 *
.heated starting length runs (see Section 3.3.3) ...... 63
3.15 Stanton number data versus non-dimensional distance along
surface for initial conditions in Figure 3.14, to study
effects of change in 64
3.16 Data for Figure 3.15, replotted versus enthalpy thickness
Reynolds number 65
3.17 Upstream velocity profiles (P/D =5, 10) for initially
low R© 5 « , heated starting length runs (see Section
3.3.4). 7 ...... 66
3.18 Upstream temperature profiles (P/D =5, 10) for initially
low Re ^9 I heated starting length runs (see Section
3.3.4). 7 . . . 67
3.19 Stanton number data (P/D = 5) versus non-dimensional dis-
tance along surface for initial conditions in Figures
3.17 and 3.18, to study effects of thin initial momentum
boundary layer 68
3.20 Data from Figure 3.19, replotted versus enthalpy thick-
ness Reynolds ntmiber 69
vll
Page
Figure
3.21 Stanton number data (P/D * 10) versus non-dimensional
distance along surface for initial conditions in Fig-
ures 3.17 and 3.18, to study effects of change in hole
spacing 70
3.22 Data from Figure 3.21, replotted versus enthalpy thick-
ness Reynolds number 71
3.23 Velocity profiles downstream of ninth blowing row (see
Figure 3,1 for boundary layer initial conditions) 72
3.24 Velocity profile obtained by spanwlse-averaging the pro-
files in Figure 3.23 73
3.25 Shear stress profile obtained using the spanwlse-averaged
velocity profile 73
3.26 Mixing-length profile obtained using the shear stress
profile and the spanwlse-averaged velocity profile .... 74
3.27 Temperature profiles downstream of ninth blowing row.
6 = 1.00 (see Figures 3.1 and 3.2 for boundary layer
initial conditions) 75
3.28 Temperature profiles downstream of ninth blowing row,
0 = 0.16 (see Figures 3.1 and 3.2 for boundary layer
initial conditions) ...... 76
3.29 Temperature profile obtained by spanwise-averaging
the profiles in Figure 3.27, 0 = 1.00 77
3.30 Temperature profile obtained by spanwlse-averaging
the profiles in Figure 3.28, 0 = 0.16 77
4.1 Prediction of St for 0 = 1.3 by applying super-
position to fundamental data sets, Figures 3.6 (plate 11) . 94
4.2 Stanton number ratios for all M 0.4 data and P/D * 5 . 95
4.3 Correlation of the Stanton number data at 0 = 1 96
4.4 Two constants used in prediction model 97
4.5 Prediction of the M = 0 and M - 0.4 data from Figure
3.3 98
4.6 Prediction of the spanwlse-averaged velocity profile from
Figure 3.24 99
viil
Figure Page
4.7 Prediction of the spanwise-averaged temperature profile
(0 = 1.00) from Figure 3.29 100
4.8 Prediction of the spanw^ise-averaged temperature profile
(0 = 0.16) from Figure 3.30 100
4.9 Extension of the M = 0.4 prediction (Figure 4.5) to 24
rows of holes to show stable behavior of injection model. . 101
4.10 Prediction of the M - 0.2 data from Figure 3.6 102
4.11 Prediction of the M - 0.4 data from Figure 3.6 103
4.12 Prediction of the M - 0.6 data from Figure 3.6 104
4.13 Prediction of the M - 0.75 data from Figure 3.6 105
4.14 Prediction of the M = 0 and M - 0.4 data from Figure
3.12 106
4.15 Prediction of the M = 0 and M - 0.4 data from Figure
3.15 107
4.16 Prediction of the M = 0 and M - 0.4 data from Figure
3.19 108
lx
List of Tables
Table Page
2.1 Energy balance closure tests 25 ;
3.1 Summary of slant-hole Injection data 35
3.2 Comparison of experimental Stanton numbers with Stanton
numbers predicted by applying superposition to experi-
mental data at 6-0,1 37
3.3 Momentum and enthalpy thickness Reynolds numbers for
the velocity and temperature profiles in Figures 3.23
through 3.30 49
X
A
c
C
CLl \
CL2 {
%
D
DELMR
supplied
power
EMIS
F
h
h
*
h
o
H
Nomenclature
heat transfer area. Including hole area (see Figure 1,2)
hole cross-sectional area (see Figure 1.2)
test section plate surface area
van Driest damping coefficient, mixing-length model
blowing parameter, F/St(0 =1)
specific heat, mainstream fluid
damping constant, equation for
constants for adjustment of (5-/6)
drag coefficient, injection model
skin friction coefficient, T = c^/2 p u£
O t oo oo
hole diameter of injection tube
van Driest damping function, mixing- length model
mass shed ratio, injection model
electrical power supplied to plate
emissivity of plate to determine q
rad
blowing fraction, / (p^U^)
drag force, injection model
proportionality constant. Newtons Second Law
heat transfer coefficient, q"/(T -T_) , with wall mass flux
(transpiration or film cooling)
heat transfer coeff icient , q / (T -T ) , with film
cooling
heat transfer coefficient, without wall mass flux
velocity profile shape factor,
xi
I
I"
J
k
K
KFL
KCONV
Jl
(Z/6)
max, a
m
M
Pr
Pr,
PD
. ”
^cond
conv
^flow
losses
^rad
static enthalpy
2
stagnation enthalpy, I + U / (2g^J)
conversion constant, mechanical to thermal energy
thermal conductivity
conductance between plate and cavity to determine
conductance to determine q^-
low
conductance- area product to determine
mix ing- leng t h
maximum mixing-length constant, turbulence-augmentation
model
mass flow rate in stream tube, injection model
blowing parameter, (P 2 U 2 ) / (P^„U^)
hole spacing, or pitch (see Figure 1.2)
pressure
Prandtl number, yc/k
turbulent Prandtl number
penetration distance, injection model
wall heat flux, q /A_ ^
^conv tot
heat transferred from plate to cavity and adjacent plates
to determine q-
^losses
heat transferred from plate by convection to define Stanton
number
heat transferred from plate to secondary air flow
heat transferred from plate other than by convection,
^cond ^ ^flow ^ ^rad
heat transferred from plate by radiation
0 33
recovery factor, Pr *
xil
Re
X
Rg52
Re^2
S
St
St
o
SAFR
T
T
g
T+
U
V
VO
+
X
y
+
y
a
6 ( )
6
hole-diameter Reynolds ntjmber, DU^/\J
X- Reynolds number, (x-x )U /v
VO °°
momentum thickness Reynolds number, 62 U^/V
enthalpy thickness Reynolds number, A„U /v
conductance between adjacent plates to determine
Stanton number, h/ (p^cU^) , see equation (2.1)
Stanton number at M = 0
Injectant flow rate through one tube
temperature
temperature of secondary air delivered to test section
non-dimensional temperature, (T-T^)‘^'cJ/ 2 V{ (T^-T^)St}
mainstream recovery temperature, + {rU^}/{2g^Jc}
velocity component , x-direction
friction velocity, , determined by Clauser plot
method
non-dimensional velocity, U/U^
velocity component, y-direction
distance along surface, measured from nozzle exit
distance, nozzle exit to virtual origin of turbulent
boundary layer
non-dimensional distance, xU^/v
distance normal to surface
non-dimensional distance, yU^/v
hole axis angle, measured from surface
uncertainty in ( )
boundary layer thickness where U/U^ = 0.99
xili
mass shed into stream tube, injection model
displacement thickness,
_ ^
p-U
^OO 00
)dy
momentum thickness.
, ) 4y
CXD
enthalpy thickness ,
eddy diffusivity for momentum
00
— )dy
adiabatic wall effectiveness, (T -T^) / (T„-T^)
temperature parameter, (T 2 **T^) /
von Karman constant, 2-d mixing-length
constant , turbulence-augmentation model
outer length scale constant, 2-d mixing-length
dynamic viscosity
kinematic viscosity
density
Stef an- Boltzmann constant
shear stress
non-dimensional shear stress, t/t
function in 0=1 data correlation, {st(0 = 1)/St }/
o
{iln(l +
stream tube, injection model
augmented value, turbulence-augmentation model
aw
eff
jet
2
adiabatic wall value in presence of film cooling
effective value
InJ ectant value
new
o
old
t
2-d
00
immediately downstream of Injection location, Injection
model
wall value (except with h or St )
o o
immediately upstream of injection location. Injection
model
turbulent value
two-dimensional value, turbulence-augmentation model
mainstream value
XV
Chapter 1
INTRODUCTION
1,1 Background for the Problem
High- temperature gases passing over a surface may result in a large
heat flux to the surface. Film cooling the exposed surface is one means
of reducing heat flux, and thus surface temperature. With this method,
coolant is injected through the surface and into the boundary layer over
the surface. Providing the coolant is distributed properly, it will act
as an effective heat sink and protect the surface from the hot mainstream
gases .
A primary use for film cooling is to protect the blades of the high-
pressure turbine component of a gas turbine engine from hot combustion
gases. Conventional film cooling may be accomplished by coolant injection
through one or more rows of slots or discrete holes in the surface or
through a porous strip in the surface. With these methods the region of
greatest blade protection is the local region domstream of the injection
sites, which are generally at the blade leading and trailing edges.
As turbine inlet gas temperature is increased in an effort to im-
prove engine thermodynamic efficiency, it v/ill become Important to cool
the high-pressure turbine blades over their entire exterior, as opposed to
locally film cooling the leading and trailing edges. This may be accom-
plished either by transpiration cooling through a porous blade surface or
by full-coverage film cooling through an array of small discrete holes
that covers the entire blade surface (Esgar 1971). In principle, either
method will allow the use of a mainstream gas temperature V7ell in excess
of that which will melt a metallic surface. At the present time, though,
transpiration cooling appears the least feasible of the two cooling
schemes, because of difficulties with the structural integrity of the
porous "skin" which forms the surface, and because of susceptibility to
pore clogging. Discrete hole, full-coverage cooling looks promising.
The work described herein is an experimental and analytical study of heat
transfer to the turbulent boundary layer over a full-coverage film-cooled
surface.
1
1.2 Full-Coverage Film Cooling
The concept of full-coverage film cooling is illustrated in Figure
1.1, showing a blade and blade cavity. The holes on the blade surface
form a staggered array; the injectant leaves the surface at an acute
angle. In the film-cooling process, coolant is delivered into the intetlor
of the blade thru an insert which forces the coolant to impinge on the
inner surface of the blade. The coolant then exits through the holes and
into the boundary layer over the surface at velocity and temperature
T^ . The mainstream velocity is , the mainstream gas temperature is
T^ , and T^ is the blade temperature.
T«
Uoo
BLADE
INSERT
Figure 1.1 Full-coverage film- cooled turbine blade and blade cavity
2
Heat transfer between a surface and the fluid flowing over the sur-
face in the presence of film cooling is affected by the hydrod 5 niamic and
thermal characteristics of the injectant and mainstream flow, the surface
thermal, boundary condition , and the coolant hole pattern and injection
angle. One Important hydrodynamic characteristic is a blowing ratio,
the ratio of the injectant-to-mainstream mass flux. This can be described
in two ways: averaged over the area of one hole.
M
^ 2^2
oo
( 1 . 1 )
or averaged over the area associated with one hole (Figure 1.2)
F
P u
^00 00
( 1 . 2 )
The thermal characteristics of the injectant and mainstream flow can be
linked to the surface thermal boundary condition,
e
(1.3)
Other useful parameters include: the ratio of boundary layer enthalpy
thickness-to-hole diameter, ; the ratio of boundary layer momentum
thickness-to-hole diameter, ^ 2 ^^ * ratio of the viscous length
scale to the hole diameter, (v/U^)/D . The cooling configuration is
described by the ratio of the hole spacing to the hole diameter, P/D ,
and by the hole axis angle, a .
A study of the fluid mechanics and heat transfer of a film-cooled
surface has been in progress at Stanford for the past several years.
The study, which includes the work reported herein, has been carried
out using flat full-coverage film-cooled surfaces. The study has been
conducted using geometrical and Reynolds number similarity to actual
film-cooled turbine blades, but not Mach number or Eckert number
similarity. Surface curvature, rotation, high mainstream turbulence,
and pressure gradient effects are not considered.
3
1.3 Heat Transfer with Film Cooling
The convective rate equation used to describe surface heat flux in
boundary-layer flows with wall mass flux is
where h is a heat-transfer coefficient and T and are wall and
o 0 °
mainstream temperatures, respectively (mainstream recovery temperature,
^ , for high-velocity flows). For film cooling, the convention ac-
cepted in the past was to alter the above equation by replacing with
, the temperature the wall would assume in the presence of film
cooling but with zero heat flux, and by replacing h with h^ , the heat
transfer coefficient without wall mass flux (film cooling)
= h (T - T )
00 aw
(1.5)
In using equation (1.5) it is assumed that h^ , the heat transfer
coefficient in the absence of film cooling, is also appropriate for use
with film cooling. Based on this assumption, most experimental investi-
gations to date (Goldstein 1971) have concentrated upon obtaining T
3.W
for various injection geometries and blowing ratios and correlating it
in terms of a film-effectiveness parameter.
n =
( 1 . 6 )
However, as pointed out by Metzger and Fletcher (1971) and others, the
heat-transfer coefficient in the region Immediately downstream of injec-
tion can be significantly different from h^ . Thus an experimental
heat transfer coefficient, h , is required to replace h^ in equation
(1.5) to predict surface heat flux.
A new approach to film cooling has been developed at Stanford, based
on equation 1.4 instead of equation 1.5 (Choe, Kays, and Moffat 1976).
This was evolved from consideration of transpiration cooling.
5
The similarities between full coverage film cooling and transpiration
cooling suggested this approach; the differences proved easy to handle.
There are two important regions on a film-cooled surface, the full-
coverage region and the downstream recovery region. The major concern
here is in the full-coverage region, i.e., the area around the holes.
Geometrically, transpiration cooling differs from full-coverage film
cooling in that with the latter the holes are usually large relative to
the boundary layer thickness and consequently the injectant temperature
is often different from the surface temperature. From a fluid mechanics
standpoint, full-coverage film cooling jets penetrate the sublayer of
the turbulent boundary layer, while with transpiration cooling the in-
jectant stays within the sublayer. From a heat transfer standpoint,
with full-coverage film cooling the surface heat flux decreases to a
minimum as the blowing rate increases. With a further increase in the
blowing rate heat flxix may begin to increase, whereas with transpiration
cooling the heat flux continuously decreases. Despite these differences
it is suggested that full-coverage film cooling be treated using the
variables found useful in transpiration cooling since, physically, transpi-
ration is a limiting case of discrete-hole, full-coverage film cooling
as hole diameter and spacing is decreased relative to boundary layer
thickness.
To approach full-coverage film cooling from the viewpoint of transpi-
ration cooling, the concepts of h and T^^^ , developed for the recovery
region downstream of a slot or row of holes are abandoned, and the heat
transfer convective rate equation (1.4) used with transpiration cooling
is employed. In this equation the heat flux is the local average over
the surface area associated with each hole (shown in Figure 1.2),
Equation (1.4) defines the heat transfer coefficient which, for the
work reported herein, can be functionally described in terms of a Stanton
number, dependent upon several parameters.
p U c
^00 00
= St
= f M, 0 , — , — » “5 , Pr , - , a , J (1.
7)
6
As mentioned above, full-coverage film cooling differs from tran-
spiration cooling in that the injectant can leave the surface with a
temperature different from the surface temperature . The heat
transfer problem Involves three temperature potentials as reflected by
the 6 parameter. With the new approach to film cooling, using equation
(1.4) to define h , the dependence of the Stanton number upon injection
temperature, or 0 , is easily described.
To obtain Stanton number as a function of 0 , experiments using
two injectant temperatures are required, with all other parameters fixed,
to provide two fundamental data sets. Then, appealing to the linearity
of the constant-property thermal energy equation, superposition is ap-
plied to determine h or St as a continuous function of 0 ,
St(0) = St(0=O) - 0 X [St (0=0) - St (0=1)] (1.8)
The 0 parameter and superposition were first defined for use with
film cooling by Metzger, Carper, and Swank (1968) in conjunction with
transient film cooling heat transfer measurements.
1.4 Literature Review
A general review of film cooling can be found in Goldstein (1971),
and a review of discrete hole film cooling is given by Choe et al. (1976).
Work done at Stanford on transpiration cooling is reviewed by Kays and
Moffat (1975). Contained in this section will be a review of experimental
and analytical works associated with full-coverage film cooling.
1.4.1 Experimental Works
LeBrocq, Launder, and Pridden (1971) studied the effects of
hole-pattern arrangement, injection angle, coolant-mainstream density
ratio, and blowing ratio on r\ . Their tests were primarily conducted
on plates with a pitch-diameter ratio of 8 . The hole patterns were in-
line and staggered, with normal injection (hole axis perpendicular to
the surface), and staggered with 45® downstream-angled injection. Re-
sults of their investigation include: the staggered hole pattern is
more effective because the jets penetrate less into the boundary layer;
7
there exists a blowing ratio for which r] is a maximum, and for higher
blowing ratios, H decreases; angled injection is more effective than
normal injection.
Launder and York (1973) studied the effects of mainstream accelera-
tion and turbulence level on r] using the staggered, 45° slant-hole
test section described in the previous paragraph. Bascially it was a
study of laminar film-cooling jets issuing into a turbulent mainstream,
and their results hinged on this fact. They found that in the presence
of an accelerated mainstream the effectiveness increases due to delayed
transition of the laminar jets. When the mainstream turbulence level
is increased, in the accelerated region, the values of n go down 10
percent. For high mainstream turbulence without acceleration the ef-
fectiveness values remain unchanged.
Metzger, Takeuchi, and Kuenstler (1973) studied both effectiveness
and heat transfer on a full-coverage surface with normal holes spaced
4.8 diameters apart and arranged in both in-line and staggered patterns.
They appear to be the first investigators to report measurements of local
heat transfer coefficients, h , within a discrete-hole array. Their
investigation concludes that a staggered pattern yields a higher r) than
*
does an in-line pattern, and that h can be 20 to 25 percent higher
than h^ (without film cooling) .
Mayle and Camarata (1975) examined the effects of hole spacing and
blov7ing ratio on heat transfer and film effectiveness for a staggered
hole array with compound-angle injection. The holes were angled 30° to
the plate surface and 45° to the mainstream with P/D values of 8, 10,
and 14. Their results include: higher effectivenesses are obtained
with P/D values of 10 and 8 than with 14, regardless of coolant-flow
ratio; there is a blowing ratio that yields a maximum ri ; the heat trans-
*
fer coefficient, h , is significantly higher than h^ and becomes
almost constant (independent of the number of rows of holes) for all M
at P/D = 8 , but only for high blowing ratios with a P/D = 10 ; and
*
past the last row of holes, h rapidly returns to h^ .
Choe, Kays, and Moffat (1976) studied the effects on heat transfer
of hole spacing, blowing ratio, mainstream velocity, and initial condi-
8
tions upstream of the discrete-hole array. They used normal injection
with a staggered array and hole spacings of 5 and 10 diameters. Stanton
number data were taken for two values of injectant temperature, corres-
ponding to 0 equal to 0 and 1 , and linear superposition was applied
to obtain Stanton number as a continuous function of injectant tempera-
ture. The data were correlated using the same parameters used with tran-
spiration investigations. Their results include: for a constant mass
flow F , a P/D of 10 produces a much-diminished cooling effect when
compared with a P/D of 5 ; in the initial region (first few rows of
holes) there is not much cooling and, in fact, St/St^ can be greater
than unity; changes of mainstream velocity and upstream initial condi-
tions have little if any effect on St/St^ ; in the downstream recovery
region, the ratio St/St^ rapidly returns to unity.
1.4.2 Analytical Works
Methods presently available to predict wall temperature, film
effectiveness, and heat transfer coefficient can be categorized into three
types: superposition of single-jet effectiveness data, boundary layer
finite-difference methods, and energy integral equation analysis.
Superposition of film-effectiveness data for individual jets to pre-
dict ri is described by Goldstein et al. (1969) and Eriksen, Eckert,
and Goldstein (1971). With the method, the injection is modeled as a
point heat source located above the wall, and a reduced form of the energy
equation is solved and normalized to give D as a function of both span-
wise and streamwise distance. Mayle and Camarata (1975) developed an
improved superposition method to predict their full-coverage data. Their
final prediction equation contained two parameters that are functions of
M and P/D .
Prediction of wall temperature and effectiveness downstream of two-
and three-dimensional film-cooling slots has been investigated by Pai
and Whitelaw (1971), and Patankar, Rastogi, and Whitelaw (1973), respec-
tively. For two-dimensional slots, the boundary layer differential equa-
tions were solved, using a mixing-length hypothesis to model the eddy vis-
cosity. The mixing- length was augmented algebraically to reflect the
large increase in turbulent mixing associated with the injection process.
9
For three-dimensional slots, the Navier-Stokes equations were reduced to
elliptic in the cross-plane and parabolic in the direction of flow and
solved numerically. Again a mixing-length hypothesis was used, with an
algebraic augmentation to account for increased turbulent mixing.
A finite-difference method for predicting flow over a full-coverage
film-cooled surface is reported by Herring (1975) . He started with the
Navier-Stokes equations and stagnation enthalpy equation and spanwise-
averaged them using a decomposition that reflects the periodic nature of
the flow in the lateral direction. Boundary layer assumptions were then
invoked to render them parabolic. The nonlinear convective terms arising
from the spanwise-averaging process were obtained from a simultaneous
solution to a set of ordinary differential equations describing a jet in
crossflow. Augmentation of the turbulent shear stress due to jet-
boundary layer interaction was considered. He reports velocity profile
predictions but no heat transfer,
Choe et al. (1976) developed both integral and differential analyses
to predict their data. For the integral analysis, they developed an
energy integral equation and successfully correlated their data for use
in the equation, in conjunction with linear superposition. They also
developed a finite-difference method for predicting heat transfer with
full-coverage film cooling, solving equations of similar form to those
given by Herring (1975). However, Choe et al, (1976) arrived at the
equations using local averaging, and used different models for the in-
jection process, the nonlinear terms, and the augmented turbulent mixing.
With local averaging, the area for averaging moves continuously over the
area associated with one hole (similar to that shown in Figure 1,2),
With this concept they were able to model the injection process as tran-
spiration rather than discrete injection. The nonlinear terms were
modeled by decomposing them into two parts, and interpreting one part to
be a contribution to increased turbulent mixing and the second part as a
momentum or energy source. The augmented turbulent mixing was modeled
using an algebraic equation. Choe et al. (1976) successfully predicted
moat of their Stanton number data for low to moderate blowing ratios and
P/D values of 5 and 10 , Two constants were used in the modeling
process.
10
I
To date, the only fully three-dimensional, finite-difference pre-
diction method is given by Bergeles, Gosman, and Launder (1975). They
developed a procedure for predicting the laminar hydrodynamic and thermal
field over a full-coverage film-cooled surface. Their numerical scheme
is a partially parabolic type, with similarities to that described by
Patankar et al. (1973), but with one very Important exception: the pres-
sure field is held in a three-dimensional array to account for local
mainstream-direction pressure gradients, especially in the vicinity of
the injection location. The solution procedure is thus an iterative type,
requiring a fairly lengthy computation time.
1.5 Objectives for the Present Research
The present study had three main objectives relating to heat trans-
fer with full-coverage film cooling.
The first objective was to provide a broad experimental data base
for use in developing integral or differential methods to predict surface
heat flux on a full-coverage film-cooled surface. The data base was to
contain spanwise-averaged heat transfer coefficients within the discrete-
hole array, and local coefficients in the downstream recovery region
past the final row of holes. Upstream Initial velocity and temperature
profiles were to accompany the data. The data were to be taken using
two test surfaces (i.e., two different hole spacings) with systematic
variation of the blowing ratio, various upstream initial conditions, and
with two values of injectant temperature at each blowing ratio.
The second objective was to provide velocity and temperature pro-
files of the boundary layer over the discrete-hole array. The velocity
profiles when spanwise-averaged would permit computation of a mixing-
length profile for use in developing a mixing-length model for differ-
ential prediction of the data. The temperature profiles when spanwise-
averaged would be used to compute enthalpy thicknesses for comparison
with those obtained from integration of the energy integral equation.
The third objective was to carry out both an integral and a differ-
ential analysis of the data. The integral analysis was to consist of
correlating the data for use in an integral energy equation prediction
11
method. The differential analysis was to develop a finite-difference
prediction method which could reproduce the experimental data base.
12
Chapter 2
EXPERIMENTAL FACILITY AND METHODOLOGY
2.1 Discrete Hole Rig
The heat transfer facility, hereafter referred to as the Discrete
Hole Rig, was designed and built specifically for the purpose of study-
ing full-coverage film cooling over a flat surface. The facility Is doc-
umented In Choe, Kays, and Moffat (1976) and In the doctoral thesis of
Choe (1975).
The Discrete Hole Rig Is a closed-loop wind tunnel which delivers
air at ambient pressure and constant temperature. The test section and
Its preplate and afterplate can be heated as much as 20®C above the
mainstream air temperature. A secondary loop of the wind tunnel delivers
the blowing air, heated or cooled, to the test section. Figure 2.1 shows
a flow schematic of the systems that comprise the Discrete Hole Rig. A
photograph is shown in Figure 2.2 .
2.1.1 Primary Air Supply System
The main loop is driven by a fan which delivers air to an
oblique header which turns the flow into a heat exchanger. The flow pas-
ses through the exchanger, a screen pack, and a contraction nozzle before
entering the tunnel test section. Flow leaves the test section via a
plenum box which serves to supply both the secondary blower and primary
fan. The test duct is 20.3 cm high by 50.8 cm wide by 3.05 m in the flow
direction. The flow entering the duct has a velocity profile that is
flat to within about 0.15 percent, and a longitudinal turbulence inten-
sity of about 0.5 percent. The tunnel velocity is controlled by changing
pulleys and belts on the fan and drive, and It can be varied in steps
from 9 m/s to 35 m/s .
The tunnel floor consists of an upstream preplate, a test section,
and a downstream afterplate. The sidewalls and topwall are plexiglass.
The topwall is flexible and is adjusted to produce the desired static
pressure distribution In the flow direction. For the experiments de-
scribed herein a zero pressure gradient, i.e., constant velocity, boundary
13
condition was used. To obtain this condition the top wall was set to
produce a uniform static pressure for each data run, with permissible
deviation of no more than 0.25 mm of water-pressure difference from the .
beginning of the test section to the downstream edge of the afterplate.
2.r. 2 Secondary Air Supply System
The secondary loop is driven by a blower which delivers air
through a flexible duct to an oblique header which turns the flow into
a secondary heat exchanger to control the blowing air temperature. The
flow passes through the exchanger, a bank of finned heaters, a screen
pack, and into a plenum box which contains an 11-pipe manifold, with
each pipe containing a valve for flow rate control.
The 11-pipe manifold splits the secondary flow into 11 channels,
one for each row of holes, and delivers it via delivery tubes to the dis-
tribution manifolds. Valves in each leg of the 11-pipe manifold regulate
the flow channel by channel. Hot-wire flowmeters installed in the de-
livery tubes measure the secondary air flow rate for each channel. Each
distribution manifold contains trim-adjust valves for assuring uniform
flow rate, within 1.5 percent, to each of the 8 or 9 tubes that supply
a row of holes in the test section. Secondary air flow rate can be
varied through pulleys and belts on the blower and drive, in conjunction
with the 11 main valves, to yield a range of blowing ratios from 0 to
1.5 over the range of mainstream velocities given in the preceding
section.
2.1.3 Test Plate Electrical Power System
The test-plate electrical power system delivers heater power
to each of 12 plates that comprise the discrete-hole test section. Power
is supplied from a 120-volt AC, l(j) source that is passed through two
voltage stabilizers and delivered to 12 step-down variable transformers.
The power is then delivered to each plate. A switching circuit allows a
wattmeter to be inserted for plate power measurements.
2.1.4 Preplate/Afterplate Heating System
The preplate and afterplate heating system is a closed-loop
hot-water system which operates with continuous water flow. Recirculated
14
water passes through two water heaters in series and is delivered to an
inlet manifold where it passes through rectangular tubes within the
plates. From the exit manifold the water is returned to the recircula-
tion pump. Water temperature is held constant using a set-point propor-
tional controller connected to one of the heaters. The rectangular tubes
are coupled to the feeder manifolds with individual tubes. This feature
allows the preplate to be disconnected from the manifolds for tests with
an unheated starting length.
2.1.5 Heat Exchanger Cooling Water System
The heat exchanger cooling system is a seml-clbsed loop system
which continuously circulates w&ter from an Insulated holding tank. Flow
rate is maintained high enough to ensure uniform temperature of the main-
stream air being cooled. The secondary air heat exchanger is also plumbed
into the system. Temperature control of the cooling water is achieved by
dumping a portion of the recirculated water and replenishing with make-up
water from a cold-water supply main.
2.2 The Test Surface
The floor of the tunnel duct constitutes the test surface, and it
is formed by three sections: a preplate, a test section, and an after-
plate. The preplate and afterplate are isolated from the test section
with balsa wood, and the three surfaces are leveled to form a continuous,
smooth surface.
2.2.1 Discrete Hole Test Section
The test section is composed of a frame and 12 plates. The
frame consists of aluminum side rails with phenolic cross ribs. It is
4 cm wider than the tunnel floor span, and 61 cm long in the flow direc-
tion. Copper plates, 0.6 cm deep by 46 cm wide by 5 cm long in the flow
direction, form the test surface, with the first plate blank and the 11
downstream plates containing alternating rows of 9 holes and 8 holes.
The blank plate serves as a guard heater for the first blowing plate.
Each of the 94 holes is connected to an individually adjusted flow tube.
The holes are each 1.03 cm diameter and are spaced on 5-dlameter centers
to form a staggered hole array. Figure 2.3 is a photograph of the array.
15
The plates are heated by resistance wires installed in slots mach-
ined into the back side of each plate. There are two resistance wires for
each plate, made of size 28 AWG Chromel wire, and bussed across one end
with copper wire to give an overall resistance of about 8 ohms. The
wire leads are connected to the test-plate electrical power system. Four
iron-constantan thermocouples, made of size 30 AWG duplex wire, are in-
stalled into each plate from the back side, with each thermocouple lo-
cated midway between two adjacent holes.
The plates are supported on phenolic cross ribs. The ribs have
steps machined into them to support the plates and contain clearance
holes for the delivery tubes, which leave the plate at a 30® angle. The
side rails contain water passages for heating, to minimize conduction
heat loss from the plates. Bottom plates with tube clearance holes close
the frame cavity. Heating water tubes on the bottom plates, parallel to
the cross ribs, serve to regulate the cavity temperature. Figure 2.4
shows a cross-sectional view of the discrete hole test section, and Fig-
ure 2.5 shows a photograph of a close-up of the test surface.
Delivery tubes for the slant-hole test section are glued into re-
cesses cut into the back side of each plate, as shown in the photograph
in Figure 2.6 . The tubes, made of linen phenolic, extend back at a 30®
angle to the plate surface for a distance of 35 cm and are then turned in
the downward direction by elbows. One tube in each plate contains an
iron-constantan thermocouple located upstream of the point where the tube
enters the frame cavity. The cavity is loosely packed with insulating
material to minimize heat loss from the back sides of the plates.
2.2.2 Preplate and Afterplate
The preplate and afterplate test surfaces are identical in
design. Each plate is formed by 48 rectangular copper tubes and
insulated on the back side. Each tube, 2.6 cm long in the flow direction,
is covered by 3 thin sheets of bakelite and a thin copper sheet. The
tubes are isolated from each other with thin spacers across the tube
span. An iron-constantan thermocouple is imbedded in the back side of
the copper sheet. Hot water can be passed through 24 tubes in each
plate for surface temperature control. The heating section of each
16
plate butts against the test section.
Surface heat flux for each water- heated tube can be measured with
a heat flux meter Installed In the middle bakellte laminate and below
the thermocouple location. Each meter Is 5 cm wide by 0.4 mm thick and
wound with multiple silver-constant an thermocouples to measure tempera-
ture difference across Its thickness.
2.3 Rig Instrumentation and Measurement
Measurements of the various physical quantities necessary to compute
Stanton numbers or velocity and temperature profiles are described In
this section. In addition, uncertainties In their measurements are given,
obtained following Kline and McCllntock (1953) .
2,3.1 Temperature
All surface temperatures, secondary air temperatures, and
the mainstream temperature were measured with iron-constantan thermo-
couples. Samples of the wire were calibrated against a precision quartz
thermometer, and the resulting calibration curves were incorporated into
the data-reduction program.
All thermocouple wires were brought to constant temperature zone
boxes at the measurement console and attached to selector switches. To
avoid sharp temperature gradients along the wires, most of the wires were
sheathed in plastic tubing from point of origin to the zone boxes.
The thermocouples were installed in the test section plates and
side rails, following Moffat (1968), to ensure adequate immersion depth.
The four thermocouples in each plate were initially used to ensure the
plate was operating at near-isothermal conditions, and then were connected
in parallel to provide an average surface temperature. The use of thick
copper plates plus the heating of the side rails to near plate temperature
gave an isothermal boundary condition.
The temperature of the mainstream air was measured with a thermo-
couple whose junction was normal to the flow. The indicated temperature
was corrected for velocity error following Moffat (1962) , and then to re-
covery gas temperature using a recovery factor equal to the air Prandtl
number raised to the one- third power. The recovery temperature was most
important in formulating the Stanton number for the = 35 m/s data.
17
where the kinetic temperature Is about 5 percent of the plate-to-maln-
stream temperature driving potential.
Uncertainty In a thermocouple measurement was 0.14°C.
2.3.2 Pressure
Tunnel static pressure and mainstream dynamic pressure were
measured with Inclined manometers. Static pressure was measured from
taps located In one of the tunnel sidewalls. The mainstream dynamic
pressure was measured with a Kiel probe. Uncertainty In these pressure
measurements was 0.25 mm water. This uncertainty also applies to the
zero pressure gradient tunnel condition (recall that this condition was
established by requiring a static pressure difference of no more than
0.25 mm of water between the upstream edge of the test section and the
downstream edge of the afterplate) .
2.3.3 Test Plate Power
Power delivered to each of the discrete-hole test plates
was measured by inserting a precision AC wattmeter into the plate power
circuit. Because the insertion changes the circuit impedance, a circuit
analysis was carried out to account for insertion loss. The analysis Is
similar to the one described in Choe (1975). The insertion-loss analysis,
along with the wattmeter calibration, is incorporated into the data-re-
ductlon program. Uncertainty In plate power measurement was 0.3 watts.
2.3.4 Afterplate Heat Flux
Heat transfer from each afterplate cell was measured by a
heat flux meter. Each meter was calibrated by Choe (1975) to account
for heat loss through the meter to adjacent plates and to the plate sur-
face, and the calibrations are incorporated Into the data-reductlon pro-
gram. Uncertainty in a heat flux meter measurement was 2 percent of cal-
culated heat flux.
2.3.5 Secondary Air Flow Rate
The hot-wire flowmeters used to measure secondary air flow
rate and their calibrations are described by Choe (1975) . Each flow-
meter consists of a constant-current heating element and a thermocouple
circuit, with the circuit measuring the temperature difference between
18
I
the upstream air and the heating element. The flowmeters are installed
at the downstream end of 2 m delivery tubes and calibrated in place.
Flowmeter calculations in the data-reduction program consider corrections
due to air property changes and zero shift. Uncertainty in secondary air
flow rate for a row of holes was about 3 percent of calculated flow rate.
2.3.6 Velocity and Temperature Profiles
Velocity profiles were obtained by traversing the boundary
layer with a round, 0.5 mm outside diameter pitot probe. The resulting
dynamic pressure was measured with a pressure transducer, calibrated with
a resulting uncertainty of about 0.05 mm of water over the pressure range
of interest. Uncertainty in velocity was about 1.5 percent of calculated
velocity.
Temperature profiles were acquired by traversing the boundary layer
with an 0.08 mm diameter chromel-constantan thermocouple probe. The
probe was calibrated using a precision quartz thermometer to give an un-
certainty in temperature of 0.08®C.
2.4 Formulation of the Heat Transfer Data
Experimental heat transfer data from the discrete-hole test section
are presented in terms of a Stanton number, defined as
St
conv
U c (T -T
tot 00 oo ' o c
( 2 , 1 )
In the above definition, ^ is the total surface area for one plate.
Including the holes; , c , and U^ are density, specific heat,
and velocity for the mainstream air; T and T are the plate tem-
o oo, r
perature and mainstream recovery temperature (see 2,3.1 for a discussion
of T ) .
00, r
The q term represents heat transferred from the test plate to
the boundary layer by forced convection. To evaluate this term (based on
total measured power) requires construction of a model for the heat trans-
fer behavior of the experimental system. The model consists of an energy
balance on the plate, summarized by:
19
xonv
^supplied ^losses
power
( 2 . 2 )
The heat losses in the above equation are decomposed into
losses
^rad ^ ^cond ^flow
(2.3)
where is thermal radiation from the plate top, *^cond heat
conduction between adjacent plates (or end plates and preplate and after-
plate) and between the plate and frame, and is heat transferred
by convection from the plate to the secondary air as it passes through
the plate.
Experimental heat transfer data from the cells that form the after-
plate are also presented in terms of a Stanton number, with equation
(2.1) modified by replacing *^conv^^tot heat flux meter signal,
appropriately converted. To obtain the heat flux, equation (2.2) was
used, with the terms considered to be on a per unit area basis. Equation
(2.3) was also used, with the loss modes considered on a per unit area
basis and neglected.
In the following sub-sections, heat loss components and the second-
ary air exit temperature will be described , along with energy balance
closure tests to validate the use of equations (2.2) and (2,3). In addi-
tion, uncertainty in the Stanton number is discussed. Values of the
constants used in the following section are contained in the Stanton Num-
ber Data Reduction Program in Appendix III.
2.4.1 Radiation Loss
Radiation from the plate top surface is modeled using
^rad
= EMI3
K ^ ^
tot
4 4
(T - T^)
o O’
(2.4)
This model assumes that the radiation shape factor is 1,0, i.e., the
plate sees only the plexiglass tunnel walls at T , and that the air
20
radiation absorption is negligible. There will be no radiation loss
from the back side of the plate because the cavity is packed with insula-
tion,
2.4.2 Conduction Loss
Heat transfer by conduction is modeled as
q , = K .• (T . - T J + S • (T . - T ._)
cond i 0,1 cavjl 1 o,i o,i+l
+ S, T • (T 4 - T ^
i— 1 0,1 o,i“±
(2.5)
where the subscripts denote the plate under consideration and its adja-
cent plates, and K and S are conductances. For the afterplate, the
lateral conductances were measured by Choe (1975) .
The S conductances between the preplate and the first test section
plate, and between the last test section plate and the afterplate, were
established by experiments of the type described by Choe (1975). A cal-
ibration unit containing three heaters in an insulated shell was placed
over the area where the test section joins the preplate (or afterplate),
with one element over the test section plate and the other elements over
the two adjacent cells. The heaters were operated in three modes: the
first with the same power to all heaters; the second with one of the
guard heaters off; the third with both guard heaters off. An energy bal-
ance for the cell adjacent to the test section plate (under the middle
heater) permitted the values for S between the cell and the plate to be
obtained.
The S conductances between adjacent plates within the test section
were calculated based on the geometries and materials involved. Heat
transfer results are not very sensitive to these values since all plates
were operated at the same temperature in any case, within a fraction of
a degree.
The K conductances between the test section plates and the frame
were established by experiments of the type described by Choe (1975).
The sidewalls and topwall were removed and a 9-cm thick styrofoam block
was placed on top of the discrete hole test section. The plates were
then heated to a uniform temperature and the frame and cavity cooled by
21
the cold water supply, resulting in a temperature difference of about
15 *C. Plate and cavity temperatures and plate power were measured and a
resulting K conductance was calculated. In the calculations, heat loss
through the styrofoam was considered to be 11 percent of the power pro-
vided (obtained from analytical considerations) .
Definition of the effective cavity temperature was based on analy-
sis of the frame and cavity temperature distribution. The frame was in-
strumented with two thermocouples each in the front and rear rails of
the frame, three thermocouples along each of the two aluminum side rails,
and one thermocouple in each of the four aluminum bottom plates. From
this resulting temperature field, coupled with analysis, it was deter-
mined that, because the cavity was composed of low thermal-conductivity
materials, base-plate temperatures had a negligible influence on the
plate conduction losses. Therefore the arithmetic average of the side-
rail temperatures were used along with linear interpolation to obtain
cavity temperatures. In fact, since the siderails and bottom plates
were heated to near plate temperature to minimize conduction losses, a
precise formulation of the cavity temperatures was not required.
Uncertainty in an experimentally obtained conductance was about
15 percent of its indicated value.
2,4.3 Secondary Air Exit Temperature
The secondary air exit temperature was different from the
inlet temperature due to heat transfer between the air and the test sec-
tion. The exit temperature is modeled by considering the system as a
heat exchanger, given by
g
where T^ is the secondary air inlet temperature, exit tem-
perature, and T is the arithmetic average of the plate and cavity tem-
peratures (defined similarly to that in the previous section but with
linear interpolation of one-third contributions from the left and right
side rails and base plate temperatures) , The secondary air flow rate
22
through the tube is SAFE, and the conductance-heat transfer area product
is KCONV, Both analysis and experiments were conducted to determine
KCONV as a function of secondary air flow rate.
In the analysis the heat exchanger problem was defined in terms of
heat transfer between the air and the tube in the cavity region, and be-
tween the air and the tube/copper lip as it passes through the plate.
The analysis was performed and the predicted total conductance-area pro-
duct, KCONV, and the partial conductance-area product, KFL (for the tube/
lip region) were graphed on log-log paper as a function of flow rate. -
Experiments were then conducted to determine KCONV (and KFL, to be dis-
cussed in the next section) . The sidewalls and topwall were removed for
the experiments, and a 9 cm-thick styrofoam block, fabricated to cover
three adjacent copper plates, was installed. Holes in the block allowed
secondary air to pass through the block. For these experiments, all
test section plates and the frame side rails were heated, while cooled
secondary air was passed through the tubes. Power supplied to the middle
of the three covered plates was measured. In addition, for one tube sup-
plying secondary air to the middle plate, the air temperature entering the
test section and leaving the styrofoam block was measured.
The experimental KCONV values were determined from equation (2.6).
These data were plotted on the analysis graph and found to be a nearly
constant percentage below the theoretical values, and thus the theoretical
KCONV curve was shifted downward to pass through the experimental points.
The theoretical KFL curve was also shifted downward by the same percentage.
Experimental uncertainty in KCONV was about 25 percent of indicated value.
2.4.4 Convection Between Plate and Secondary Air
Heat transferred by convection between the plate and second-
ary air as it passes through the plate is modeled as
^£low “ (2.7)
where T^ is the plate temperature, T 2 is the secondary air exit tem-
perature, and KFL is a conductance. ' .
23
The experimental KFL values were determined from equation (2,7),
using the experimental procedure described in the preceding section. In
the calculation, plate power minus the power at no-flow
conditions (obtained from the zero intercept of a plate power versus
flow rate graph) . The exit temperature was used in the definition for
convenience. In principle, the secondary air temperature changes
slightly while passing through the plate area, but this is insignificant
because the temperature driving potential is either nominally zero, or
10-20®C.
The experimental KFL values, divided by the number of holes in the
row, were plotted on the graph containing the theoretical KFL (discussed
in the previous section), and they agreed within 10 to 15 percent. Ex-
perimental uncertainty in KFL was about 25 percent of indicated value.
2.4.5 Energy Balance Closure
The Stanton number is determined by measuring plate power in-
put, corrected for wattmeter calibration and insertion losses, and sub-
tracting the heat losses. The energy loss modes were modeled and incor-
porated into the data-reduction program shown in Appendix III. Energy
balance closure tests were conducted to assess the validity of the models
used to calculate the energy loss modes for the test section. In these
tests the tunnel was operated without mainstream cooling, and the plate
power was adjusted to bring each plate up to the mainstream temperature.
Cold water was used to cool the frame of the test section, resulting in
a plate-to-f rame temperature potential of about 10®C. Tests were con-
ducted for M = 0 , M = 0.41 , and M = 0.59 . For the blowing runs,
the secondary air temperature was within 0.6®C of the plate temperature.
The thermal boundary conditions for these tests were designed primarily
to check the conduction loss constants. Similar tests with 6=0 were
not possible due to the configuration of the heat exchanger cooling sys-
tem.
The closure tests showed how much energy imbalance existed for a
given set of conditions and evaluated the accuracy of the energy measure-
ment system. In principle, when equation (2.2) is evaluated for these
conditions, it should sum to zero. The results of these tests, shown in
24
Table 2.1, indicate closure to within + 0.24 watts (typical power sup—
plied to each plate during a Stanton number run was 12 to 20 watts).
The energy imbalance can be converted to a Stanton number uncertainty,
6st
6E
c (T -T
tot o
( 2 . 8 )
To evaluate this equation, typical operating values of 13°C for (T^-T^ ^)
and 16.8 m/s for were used, along with properties for air. This
converts to a Stanton number uncertainty, 6St , of + 4 x 10 ^ ,
Table 2.1
Energy balance closure tests
Plate
M
= 0
M =
0.41
M =
0.59
6E
(watts)
6St
6E
(watts)
6St
6E
(watts)
6St
1
-.24
-.424E-04
.01
.255E-05
-.05
-.979E-05
2
.09
.157E-04
-.05
-.927E-05
.10
.188E-04
3
.01
.239E-05
00
O
1
-.148E-04
.08
. 148E-04
4
.12
.218E-04
-.05
-.92 IE- 05
.08
. 140E-04
5
.06
.104E-04
1
o
-.164E-04
.06
.103E-04
6
-.11
-.208E-04
-.08
-.152E-04
.11
. 206E-04
7
-.01
-.195E-05
.03
.620E-05
.07
.126E-04
8
-.10
-.172E-04
0.
0.
-.02
-.328E-05
9
-.15
-.277E-04
1
o
-.127E-04
.14
. 261E-04
10
-.19
-.333E-04
-.12
-.228E-04
.15
.276E-04
11
-.20
-.360E-04
1
o
Ln
-.960E-05
.21
.386E-04
12
-
-
-.07
-.136E-04
.22
.389E-04
Using the procedure of Kline and McClintock (1953) for propagation
of uncertainties through equation (2.2) and (2,3) to evaluate Stanton
25
number, uncertainty bands on the data are predicted to be + 2.5% for
0 “ 1 and + 5% for 0=0. The uncertainty analysis is in agreement
with the energy balance closure tests for 0 - 1 . The larger uncertainty
band for 0=0 reflects uncertainty in the plate-secondary air loss
constants,
2,5 Rig Qualification
Once the energy balances were established, it was possible to run
baseline checks for the hydrodynamic and heat transfer performance.
Earlier qualification tests of this apparatus were reported by Choe et
al. (1976).
2.5.1 Hydrodynamics
The hydrodynamic qualification consisted of determining that
the tunnel flow was two-dimensional and that the approaching boundary
layer velocity profiles were typically turbulent.
Two-dimensionality of the tunnel was examined by measuring the
boundary layer momentum thickness at five locations across the span over
the midpoint of the test section guard plate. The thicknesses were found
to be uniform within 2 percent for the case of no injection at a uniform
tunnel velocity of 16.8 m/s , For the low momentum thickness Reynolds
number runs, the flow was accelerated over the preplate and recovered to
zero pressure gradient over the test section and afterplate. For these
conditions, the momentum thickness uniformity was within 10 percent.
Figure 2,7 shows the topwall configurations and boundary layer trip loca-
tions for these two types of runs.
Velocity profile qualification consisted of examining the experimental
profiles, checking for accepted behavior in the logarithmic and wake re-
gions, and comparing with accepted correlations. In addition, profile
shape factors were measured. These comparisons are shown on the profile
graphs that accompany the Stanton number runs for M = 0 (given in the
+ +
next chapter). They are plotted in "wall coordinates", U versus y
+ +
The skin friction coefficient, used to form U and y , was found by
fitting the velocity data to a logarithmic law-of-the-wall in the range
of 75 to 125 for y*** (Clauser plot) . Velocity profiles for the low
26
momentum thickness Reynolds number cases are not plotted in wall coordi-
nates because the flow was still transitional, as evidenced by the high
shape factors.
For each Stanton number run, a velocity profile was taken over the
guard plate midpoint to obtain the initial momentum thickness Reynolds
number. From this information the turbulent boundary layer virtual ori-
gin was computed, using a relation between momentum thickness and dis-
tance, X . This relation, given in Kays (1966), is derived by inte-
grating the momentum integral equation with a power-law velocity profile
assumption.
Experimental momentum thicknesses on the guard plate were found to
increase as M increased, due to the downstream flow blockage effects
from the secondary air injection. This resulted in a slight decrease in
the virtual origin with increasing M . To facilitate comparison of the
data at the same x location, the virtual origin from the M = 0 veloc-
ity profile was used to compute x- Reynolds numbers for a given data set,
2,5.2 Heat Transfer
The heat transfer qualification consisted of comparing the
unblown Stanton number data (the M = 0 run for a given data set) with
accepted correlations for two-dimensional equilibrium flow over a smooth
plate with constant wall temperature (see, for instance, Kays 1966). Ad-
ditional comparisons were made between the unblown Stanton number data
and predicted results using a boundary layer computer program.
The comparison of data with accepted correlations is shown on the
graphs in the next chapter and discussed there as well. The comparisons
are, perhaps, most meaningful for the data that are plotted in enthalpy
thickness Reynolds number coordinates. The enthalpy thickness for those
graphs are computed from the energy Integral equation for constant prop-
erties and constant wall temperatures, as derived by Choe et al. (1976).
— - = St + F X 0 (2.9)
dRe
X
27
00 2 CO
where Re ^2 ~ d(Re^) = dx . The interval of integration
for the above equation, to determine Re/^ 2 (^) » from the midpoint of
the upstream plate to the midpoint of the next downstream plate, to de-
fine the enthalpy thickness Reynolds number at that downstream location.
The unblown Stanton number data were nominally 5-7 percent above the
baseline correlations in the blowing region for the P/D - 5 case. For
the case of P/D = 10 , alternate holes and alternate rows in the test
section were plugged, thus producing a much smoother surface with every
other row completely smooth. The Stanton number deviation was nominally
3 percent for the P/D = 10 unblown case for the plates containing holes,
with almost no Stanton number deviation on those plates that were com-
pletely plugged.
28
ro
VO
Figure 2.1 Flow schematic of wind tunnel facility, the Discrete Hole
Rig
Figure 2.3 Photograph of slant-hole Injection test surface, showing
staggered hole array
30
CAVITY
HEATING
TUBE
Figure 2. '4 Cross-sectional drawing of the discrete hole test section
# I CONFIGURATION
BOUNDARY UNBLOWN, BLOWING UNBLOWN,
LAYER TRJP SERVES TO CONTROL SECTION HEATED
' A, GROWTH
I ^
I
i
to
to
7^2 CONFIGURATION
BOUNDARY LAYER TRIP
Figure 2.7 Configurations for tunnel topwall and boundary layer trip: #1 is'^ for thick initial
boundary layer; #2 is for thin initial boundary layer
Chapter 3
EXPERIMENTAL DATA
3.1 Types of Data
The primary emphasis of the experimental program was the acquisi-
tion of Stanton number data for a wide range of initial conditions and
blowing ratios, and two injectant temperatures at each blowing ratio.
The data were acquired for full-coverage surfaces with two different hole
spacings, and for the recovery region downstream of the full-coverage sur-
face. Mean velocity and temperature profiles of the boundary layer up-
stream of the blowing region were obtained to accompany the Stanton number
runs. Table 3.1 summarizes the data.
A secondary emphasis of the experimental program was the acquisition
of a series of mean velocity and temperature profiles within the blowing
region, behind a hole in the ninth blowing row. The profiles were taken
for one set of initial conditions and for one blowing ratio and two in-
jectant temperatures at that set of conditions.
3. 2 Description of the Stanton Number Data
The primary investigation was a study of the effects of the blowing
ratio on Stanton number for a hole spacing-to-hole diameter ratio of 5 .
The tests were carried out with a mainstream velocity of about 16.8 m/s
and an initial momentum thickness Reynolds number of about 2700 (in all
data reported, initial conditions are those of the boundary layer over
the midpoint of the upstream guard plate) . In these tests an unheated
thermal starting length was used to give a well-defined initial thermal
condition (recall only the downstream half of the preplate could be heat-
ed) .
To determine the effects on Stanton number of a thick thermal
boundary layer at the upstream edge of the blowing region, data at a
single value of M were taken for the hydrodynamic condition described
above and with the preplate heated. The initial enthalpy thickness
Reynolds number for the test with heating was about 1800. The effects of
34
Table 3.1
Summary of slant-hole injection data
(note, and R®A2 upstream initial conditions
at guard plate midpoint)
30® slant-hole injection
Unheated Preplate
Partly
Heated
Preplate
Heated
Preplate
U^(m/s)
9.8
16.8
34.2
16.8
11.8
^S2
1900
4700
2700
515
1 ^
70
100
160
1800
490
P/D
5
10
5
D
5
10
5
10
5
10
M = 0
X
X
X
X
X
X
M = 0.2
X
M = 0. 4
X
X
X
X
X
X
M = 0.75
X
X
X
X
M = 0.95
X
M = 1.30
X
hole spacing on Stanton number were examined (for the hydrodynamic
condition mentioned above) by reconfiguring the hole array to P/D = 10
using plugs. For these tests an unheated starting length initial condition
was used, and tests were conducted at two blowing ratios.
The effects on Stanton number of changing the initial hydrodynamic
boundary layer were examined in two ways: (1) Tests were conducted with
a single blowing ratio, P/D = 5 , and upstream initial conditions
35
of Reg 2 ~ 1900 and 4700 and an unheated starting length. Initial
boundary layer thickness-to-hole diameter ratios for these tests varied
from 2,4 down to 1.9, and the tests were primarily considered to be an
examination of the effects of changing the mainstream velocity, or hole
diameter Reynolds number, RCj^ ^ . (2) Tests were conducted with two
values of blowing ratio M , for P/D = 5 and 10 , and upstream initial
conditions of Reg 2 ” ~ initial boundary layer thickness
was about 0.5 hole diameters, and the tests were designed to examine the
effects of a very thin upstream boundary layer.
At each blowing ratio, data runs were taken with two Injectant tem-
peratures: 0.0 ^ 0 ^ 0.1 , corresponding to a mainstream-temperature
fluid and 0.9 0 <_ 1.1 , corresponding to surface-temperature fluid.
The linear superposition equation (1.8) was then applied to the two data
runs (for a given M ) to adjust the data to Stanton numbers at 0=0,
1 , To adjust the recovery region data, the average value of 0 for
blowing rows 10 and 11 were used. The validity of the superposition
principle was checked by acquiring data at M = 0.3 and 0 ~ 0 , 1 and
1.26 and comparing Stanton number predicted by superposition at 0 - 1.26
with the experimental data at 0 = 1.26 . The results are shown in Table
3.2 .
The data shown in the graphs are the superposition-adjusted data at
0=0,1. A tabular form of all the unadjusted Stanton number data,
along with their adjusted values (which are plotted) are given in Ap-
pendix I.
The Stanton number data have been plotted versus x-Reynolds number
and enthalpy thickness Re 3 molds number. The x-Re 3 Tiolds number is a con-
venient non dimensional x coordinate that shows Stanton number as a
function of M and 0 for the same x location on the test surface.
Enthalpy thickness Reynolds number reflects the energy content of the
boundary layer and is perhaps most meaningful for the 0=1 data plots.
Determination of the virtual origin for Re , and the enthalpy thickness
for R®A?. » discussed in Sections 2.5.1 and 2„5.2 .
On the Stanton number graphs, the first 12 points are for the test
section plates. An arrow denotes the twelfth data point. The
remaining points are for every other recovery region plate. As in-
dicated in Section 2.5.2, the reference lines shown on the x-Reynolds
36
II
I I
I III
Table 3.2
Comparison of experimental Stanton numbers with Stanton numbers
predicted by applying superposition to experimental data at 0-0,1
Plate
St(0 - 1.26)
experimental
St(0 = 1.26)
theoretical
Error
%
2
.00250
.00249
- 0.4
3
.00178
.00180
+ 1.1
4
.00147
.00148
+ 0.6
5
.00136
.00139
+ 2.2
6
.00129...
.00124
- 3.9
7
.00118
.00118
0
8
.00113
.00114
+ 0.9
9
.00104.. ,
.00102
- 1.9
10
.00102
.00097
- 5.0
11
.00095
.00093
- 2.1
12
.00093
.00093
0
15
.00114
.00106
- 7.0
18
.00118
.00116
- 1.7
21
.00118
.00116
- 1.7
24
.00120
.00118
- 1.7
27
.00126
.00124
- 1.6
30
.00133
.00128
- 3.8
33
.00132
.00131
- 0.8
number and enthalpy thickness Re3molds number graphs are accepted cor-
relations for two-dimensional equilibrium flow over a smooth plate with
constant wall temperature and hydrodynamic and thermal boundary layers
beginning at the same point.
3. 3 Stanton Number Data
The experimental Stanton number data have been segregated into four
sections for discussion. Certain data trends are common to all the data;
these will be discussed in detail only in Section 3.3.1. More complete
analysis of the data will be found in Chapter 4.
37
3.3.1 Thick Initial Boundary Layer with Heated Starting Length
The first data set to be discussed is for M = 0 and for
M « 0.4 . The trends exemplify the general behavior common to all of
the full-coverage Stanton number data sets which follow. Also, the M= 0,4
blowing ratio for this data set will be common to all the data sets which
follow. Initial conditions of the boundary layer for this set were
Re $2 “ 2700 and R^A 2 ~ 1800 .
M = 0, The first data obtained in each data set were with
M = 0 to establish a baseline. Figure 3.1 shows the initial velocity
profile over the midpoint of the guard plate for this run, and Figure
3.2 shows the initial temperature profile. Information concerning the
profiles is given in the profile graphs. The velocity profile is seen
to be a typical turbulent boundary layer profile, with a boundary layer
thickness of about two hole diameters. The Stanton number data are plot-
ted versus Re^ in Figure 3.3, and versus Figure 3,4 . In the
latter figure, the data are seen to rise 8 to 10 percent above the gen-
erally accepted St^ curve, hereafter called the equilibrium line. This
is attributed to a roughness effect of the open holes on the boundary
layer. In the recovery region the Stanton number drops to within two per-
cent of the equilibrium line within a few boundary layer thicknesses.
The roughness effect will be seen more clearly in conjunction with the
P/D = 10 data in Section 3.3.4 .
6=1 (T„ = T ). In Figure 3.3 (Re ) the Stanton number
2 o X
is seen to drop 10 percent below St^ for the first blowing plate and
30 percent below St^ for the second plate. This 10 and 30 percent drop
is common to all P/D = 5 data and low M , and it is discussed in Ap-
pendix IV, The Stanton number continues to monotonically decrease
throughout the blowing region. In the recovery region Stanton number
shows a gradual rise. The data are replotted in Figure 3.4 (Re^ 2 ) •
There is a wide spacing between data points because the injectant
greatly increases the enthalpy content of the boundary layer. By the
end of the blowing section ^®A 2 “ 10,000 , and the momentum boundary
layer thickness was 6 to 7 cm .
38
The boundary layer is highly non-equilibrium at the end of the blow-
ing section, and over the 60 cm recovery region test plate (about 10
boundary layer thicknesses) the Stanton number does not recover to the
equilibrium line. The retarded recovery is related to the excess enthalpy
content of the thermal profile associated with a momentum boundary layer
that does not have the turbulent transport necessary to diffuse the pro-
file. This is discussed in more detail in Chapter 4.
The monotonic decrease in Stanton number in the blowing region is
also typical of transpiration cooling. The two cooling schemes can be
compared for any M by computing an equivalent blowing fraction, F ,
using equation (1.2), Transpiration Stanton numbers as a function of F
can be found in Kays and Moffat (1975). For all low M data the St(0 =
1) data for discrete hole injection are much higher than the equivalent
transpiration Stanton numbers. Blowing at M = 0.4 with P/D = 5 con-
verts to F = 0,012 , which would "blow off" a transpiration boundary lay-
er, producing zero heat flux.
0 - 0 (T 2 - ^ 00 ^* Figure 3.3 Stanton number
rises for the first few blowing rows and then drops down slightly and
levels out to an almost asymptotic value, independent of the number of
rows of holes. The asymptotic behavior is exhibited by all of the slant-
hole data for 0,4 at P/D = 5 , and for M = 0.8 at P/D = 10 .
For the recovery region, once the intense mixing from the jet-mainstream
interaction is removed, the Stanton number rapidly drops below the St^
data over a distance of about five boundary layer thicknesses, and then
returns towards the St^ data. The drop is in response to a much-
thickened boundary layer without increased turbulent mixing. The data
are replotted in Figure 3.4 (Re^ 2 ) • closely spaced data reflect
the fact that the mainstream-temperature injectant does not increase the
enthalpy content of the boundary layer (see equation 2.9). In the recovery
region, the boundary layer rapidly adjusts to no-blowing conditions. A
similar fast adjustment is seen in transpiration cooling data (Kays and
Moffat 1975). By the end of the recovery region the boundary layer has
almost returned to the equilibrium line.
39
Asymptotic behavior for the 6=0 thermal condition was also ob-
served by Mayle and Camarata (1975) for compound-angle injection with
P/D = 8 and 10 and moderate M , They write, in explanation:
"This indicates that the flow field near the sur-
face is streamwise periodic and dominated by the jets.
Thus, it appears that as the hole spacing is decreased
or the coolant flow increased, a transition is grad-
ually made in which the usual streamwise growth of the
themal boundary layer yields to a periodic growth gov-
erned by the jets."
This assessment seems plausible. However, as will be discussed in Chap-
ter 4, it is believed that the phenomenon of a nearly constant Stanton
number also implies a nearly constant turbulent transport or eddy vis-
cosity/conductivity with respect to the streamwise direction, independent
of boundary layer growth. Appendix V contains a discussion of a possible
similar type of asymptotic behavior for the 0=1 data, along with a
discussion of possible jet coalescence, which might contribute to it.
3.3.2 Thick Initial Boundary Layer with Unheated Starting Length
The second data set to be discussed is the most comprehensive
set in that it formed the basis for the study of the effects of blowing
ratio and hole spacing on Stanton number. This data set includes P/D of
5 and 10 with the initial ~ 2700 and an unheated starting length.
M = 0. The initial velocity profiles for the unblown Stanton
number runs are shown in Figure 3.5 . The St^ data are plotted versus
Re and Re^„ in Figures 3.6 through 3.10 . In the Re^„ plots the
data approach the equilibrium line and pass slightly above it near the
downstream edge of the test section. The approach from below is indicative
of an unheated starting length, and the pass over the line, coupled with
the drop in the recovery region, again suggests the roughness effect on
Stanton number due to the discrete holes. The roughness effect is dimin-
ished, though, for the wider hole spacing.
0=1 (T^ = Figure 3.6 Stanton number data
are plotted for P/D = 5 and with M varying from 0 to 1,2
in increments of 0.2 , In the blowing region M = 0,18 yields the
40
lowest Stanton number over the first three plates, with M = 0.37 pro-
ducing the lowest value over the rest of the blowing region. Note the
10 percent and 30 percent drop in St for the first two blowing rows.
Values of M greater than 0.37 cause the Stanton number to rise above
the minimum values, with M = 1.21 causing the Stanton number to pass
above the M = 0 curve over most of the blowing region. This increase
in Stanton number with increase in blowing is attributed to the jets
penetrating farther into the boundary layer to provide less protection
and to increase the turbulent mixing. In the downstream recovery region
the Stanton number data appear to rise immediately for M = 0.18 and to
remain unchanged for M = 0.37 . For all larger M the Stanton number
continues to decrease throughout the recovery region. The recovery
region flow length is about 63 cm. Thus, for a 6 of 5 to 7 cm at the
start of this region, the recovery flow length for the data is about 9 to
12 6 . These data are replotted in Figure 3.7 (Re^ 2 ) •
M = 0.18 and 0.37 data lie below the two-dimensional equilibrium line
in a manner characteristic of transpiration-cooled surfaces. Data for
M - 0.52 lie near the equilibrium line, with all larger values of M
lying above the equilibrium line. In the recovery region the data for
M £ O.A appear to be returning to the equilibrium line. For higher blow-
ing, the data trend is uncertain.
The P/D = 10 data are shown plotted versus Re^ in Figure 3.9 .
The M = 0.36 data produce a minimum Stanton number in the blown region
with the M = 0.75 data lying above the low blowing ratio data. Stanton
number variation in the blowing region is due to alternate rows of holes
being plugged. The data from Figure 3.9 are replotted in Figure 3.10
(Re^^) • the recovery region, the Stanton number for M = 0.36 and
0=1 is seen to return to the equilibrium line. However, the recovery
region data for M = 0,75 and 6=1 appear not to be returning to the
line. This is attributed to a problem with the heat flux sensor response
to a three-dimensional flow in the recovery region. For P/D = 10 and
high M , the flow should be much more three-dimensional than its counter-
part at P/D = 5 , primarily due to increased jet penetration because of
the "individuality" of the jets for the wider spacing. Because the flow
41
width for "averaging" of the heat flux with afterplate is 5 cm and the
discrete holes are spaced about 10 cm apart, any three-dimensional ef-
fects will greatly affect the sensor. A similar anomaly was seen by
Choe et al. (1976) for the data set obtained with natural transition over
the blowing region, indicating the heat flux sensors were not responding
to give a spanwise-averaged heat transfer coefficient, when compared to
the test section plate values.
Visual comparison of the P/D = 10 data with the P/D = 5 data re-
veals that the major effect of increased hole spacing is to reduce the
effect of blowing i.e. to reduce the Stanton number departure from St .
o
Stanton number is the nondimens ional heat transfer coefficient, averaged
over the area associated with one hole. This area increases by a factor
of four for the increased hole spacing, and thus there is much less cover-
age for each jet. There are two bases for comparison of heat transfer
performance of the two P/D surface configurations. The first basis is
at the same blowing ratio, M , and the second basis is at the same blow-
ing fraction, F . At a specified F , the same mass flow of coolant
will be injected for the two P/D surfaces to provide protection. The
data for P/D = 5 , 10 will be compared on an F basis in Chapter 4.
0 = 0 (T^ = Figure 3.6 Stanton number data
are plotted for P/D = 5 . In the blowing region the M = 0.2 and 0.4
data have a pattern that is different from the higher blowing ratio data.
The M = 0.20 curve follows the M = 0 curve over the first eight blow-
ing rows and then gradually diverges. The M = 0,40 curve follows the
M = 0 curve over the first four blowing plates before diverging. For
all higher values of M the data depart abruptly from St^ after the
second data point. In the downstream blowing region the curves exhibit
an as 5 rmptotic behavior, indicating that a local equilibrium has been
established between the surface and the fluid in the near-wall region.
In the recovery region the data for M = 0.2 and 0.4 immediately dip
below the M = 0 curve. For M ^ 0.58 the Stanton number data decrease
much more slowly in the recovery region, and for M ^ 0,93 the data lie
above the M = 0 curve over the entire recovery region. The data are
replotted versus R©A 2 Figure 3.8 . Most of the data lie above the
42
two-dimensional equilibrium line in the blowing region. For M _< 0,4
the data dip below the reference line in the Initial recovery region,
and then appear to return toward it. Trends in the data are uncertain
for higher blowing ratios, but they appear to be returning toward the
equilibrium line.
In the initial blowing region for high blowing ratios, the Stanton
number is seen to rise and then drop back towards its eventual asymptote.
A similar Stanton number rise is seen in the initial blowing rows for
the 0=1 data. This behavior may be due to less jet penetration,
coupled with increased turbulent mixing in the near-wall region. Flow
visualization photographs by Colladay and Russell (1975) support the
less penetration idea, and the computer predictions in Chapter 4 support
the Increased mixing idea. Physically, there should be higher upstream
boundary layer momentum in the near-wall region to turn the jets. As
the boundary layer flows over the rows of holes, though, a larger
boundary layer momentxim deficit is created, and the jets are able to
penetrate farther into the boundary layer before being turned into the
downstream direction.
The P/D = 10 data are shown plotted versus Re^ in Figure 3.9
and versus Re /^2 Figure 3.10. The data for the high blowing ratio
do not appear to reach an as 3 miptote, whereas the data at the same M
and P/D =5 do reach an asymptote. This is partly attributed to the
unheated starting length initial condition. The same type of tests
were conducted at P/D of 5 and 10 with a heated starting length,
discussed in the following section,
3.3.3 Thick Initial Boundary Layer with Change in Mainstream
Velocity
The third data set to be discussed is part of the study of
the effects on Stanton number of changes in the upstream hydrodynamic
boundary layer. For this data set, obtained on the P/D = 5 surface,
blowing ratios of M = 0 and M = 0.4 were used, and initial conditions
were ^©$2 ~ 1900 and 4700 and an unheated starting length.
M = 0, Initial velocity profiles for the ~ 1900 data
and R^(S2 ~ ^700 data are shown in Figures 3.11 and 3.14, respectively.
43
Parameters for these boundary layers are compared with the ^^^2 ~
profile parameters (discussed in Sections 3.3.1 and 3.3.2), as shown below
1
Re52(inl.)
Ucx. ;■
(m/s) ;;
D ,00
^99/^
62 /D
70
1900
9.8
6500
2.4
.30
100 )
1800/
2700
16.8
11200
2.0
.23
160
4 700
34.2
A
1
j 22400
1.9
.21
In 't-be above table, Re_ is a hole-diameter Reynolds number, Re_ ^ =
» D,oo D,°°
UqoD/’^, (see Section 4.2 for a discussion of this Reynolds number). The
three boundary layers have about the same thickness ratios, while the
mainstream velocity is significantly different for the three runs.
6 = 1 (T 2 == T^) . The initial ^^62 ~ 1900 data are plotted
in Figure 3.12 3.13 (Re/;^^) • l^e initial Re ^2 ~ 4700 data
are plotted in Figure 3.15 3.16 (ReA 2 ) • All of the data
drop below the St^ data in the blowing region and indicate a slight
rise in the recovery region. The trend is identical to the initial
Re 52 “ 2700 data of Section 3.3.1 .
6=0 (T^ = T^) . The initial ^^62 ~ 1900 data are plotted
in ^ Figure 3.12 3.13 (ReA 2 ) • Tbe Stanton number is seen to
depart from the St^ data after the first blowing row, and in the re-
covery region it dips significantly below the St^ data before returning.
The Initial ^^62 ~ ^700 data are plotted in Figure 3.15
3.16 ' (Re^ 2 ) • data are seen to follow the St^ data for about,
five blowing rows before departing, and in the recovery region the Stan-
ton number returns to the equilibrium line without dipping below it.
The response of the Stanton number to 6=0 injectant and M =
0.4 is entirely different for each of the four initial conditions dis-
cussed to this point. In all cases the Stanton number data for 6=0
appear not to reflect the presence of the mainstream-temperature inject-
ant (at least for low M ) until the thermal boundary layer grows beyond
the penetration distance of the Injectant. For the initial condition of
44
an unheated starting length and for the first few rows of holes, the
thermal boundary layer was extremely thin when compared to the diameter
of the jet. For this initial condition, St(0 = 0) - St^ until the
thermal boundary layer thickens. For the heated starting length data
of Section 3.3.1, St(0 = 0) >> St^ beginning with the second blowing
plate, reflecting the already existing thermal layer. The various data
at M = 0.4 will be compared in Chapter 4.
3.3.4 Thin Initial Boundary Layer with Heated Starting Length
The last data set to be discussed is the second part of the
study of the effects of the upstream hydrodynamics. This data set was
obtained on the P/D = 5 and 10 surfaces, and the initial conditions
were ^^62 ~ ^^^2 ~ •
M = 0. Figure 3.17 shows two initial velocity profiles,
taken for the St^ data runs, and Figure 3.18 shows corresponding tem-
perature profiles. The profiles exhibit outer region similarity, but
the inner region differences, plus the shape factor information for the
velocity profiles, indicate the flow is still probably transitional on
the guard plate (the virtual origin is about 19 cm upstream) . The St^
data in Figures 3.19 through 3.22 indicate, however, that by time the
second plate is reached, the flow is completely turbulent and the boundary
layer is an equilibrium layer (see Section 2,5.1 for a discussion of how
the thin boundary layer was obtained) . The initial boundary layer thick-
ness is about one-half of one hole diameter, while the mainstream veloc-
ity is midway between that for the ^^62 ~ 1900 and 2700 boundary
layers.
The St^ data for P/D = 5 are seen to be about 8 to 10 percent
above the equilibrium line in the test plate region, and for P/D = 10 ,
the St^ data lie on the equilibrium line. Presumably the difference
is due to the effect of hole roughness on the boundary layer; with
this wide hole spacing, 71 percent of the holes were plugged, thus yield-
ing an effectively smoother surface. Note that the alternate data
points in the blowing region (where all the holes in the blowing row are
plugged) deviate even less. The St^ data in the recovery region are
seen to lie slightly below the equilibrium lines, in either Re^ or
45
coordinates, partly because no variable property correction has
been applied to the data. This correction, for an experimental AT of
about 15®C is about 2 percent (see Kays 1966) .
0=1 (T^ = T^) . The data for P/D = 5 are plotted in
Figure 3.19 3.20 . The data trend is the same as
that exhibited by the Re <52 - 2700 data in Figure 3.3 or 3.6 . The
M = 0.4 data provide the lowest values of Stanton number, with higher
blowing ratios causing an increase in Stanton number over the blowing
region. In the recovery region, the M = 0.4 data level out, while
Stanton number for the higher blowing ratio drops, indicative of a much-
thickened thermal boundary layer. The P/D = 10 data are plotted in
Figure 3.21 3.22 . The major effect of the increased
hole spacing is, again, a much diminished departure of the Stanton number
from St
o
6=0 (T 2 = T^) . The data for P/D = 5 are plotted in
Figure 3.19 data trend follows that of Figure 3.3 for a
heated starting length condition in that it reaches an asymptote, inde-
pendent of the number of blowing rows. In the recovery region, the Stan-
ton number appears to be slower in returning to the equilibrium line when
compared to the high Reynolds number data of Figure 3.3 . The data are
replotted in Figure 3.20 (Re/^ 2 ) • The slow return to equilibrium can
be more easily seen in this graph. This apparent slow return may be due
to the thin momentum boundary layer and its effect on the turbulent mix-
ing. During the course of prediction of the M = 0.4 data (see Chapter
4) , the same two "model constants" satisfactorily predicted the initial
Re ^ 2 - 1900 , 2700 , and 4700 data, with either heated or unheated
starting length, but the mixing length model constant was low for the
initial 2 ~ data. This result, coupled with the slow return of
St to equilibrium downstream of the blowing region, may be an indication
of a different turbulent structure for a boundary layer whose thickness
is on the order of the diameter of the jets.
The P/D = 10 data are plotted in Figure 3.21 3.22
(Re/^ 2 ) • Visual comparison with the P/D = 5 data of Figures 3,19 and
3.20 reveals again (see Section 3.3.2 for a parallel study and discussion
46
at high Re 52 ) that the major effect of increased hole spacing is to re-
duce the overall level of the Stanton number departure from St^ . The
data for P/D = 5 and 10 will be compared on a blowing fraction basis
in Chapter 4.
3 . 4 S panwise Velocity and Temperature Profiles
The boundary layer over the film-cooled surface was probed to ob-
tain profiles for use in developing a mixing-length turbulence model,
and for confirmation of computed Re^ 2 ^^) from equation 2.9 . The pro-
file data were obtained for initial and boundary conditions of the data
set described in Section 3.3,1 (Re<52 ~ 2700 , Re ^2 ~ 1800 , M = 0.4 ,
and 0 = 0, 1) . The profile data are tabulated in Appendix II.
Figure 3.23 shows 11 velocity profiles acquired downstream of an in-
jection hole in the ninth blowing row, along with a sketch of the loca-
tions where they were acquired. The profiles were taken with isothermal
conditions to eliminate variable property effects. Profiles 1 and 11,
2 and 10, 3 and 9, etc., would be identical if the flow were perfectly
symmetrical. Note that locations 1, 6, and 11 are symmetry line loca-
tions for the discrete hole array. Comparison of profiles 1 and 11 show
the flow is indeed S3numetrical at these locations, but at the intermed-
iate locations, a slight lack of symmetry is found. Uncertainty in the
experimentally-acquired profiles is 5-10 percent in the near-wall region
because of uncertainty in the static pressure field around the jets
(especially for profiles 5 through 7) .
Profiles 1 and 11, taken five hole diameters downstream of an in-
jection site, show the presence of the upstream jet. It is attached to
the wall with a peak velocity of about 0,5 , whereas the fluid was
injected with a velocity of 0.4 , This increased velocity is in
response to conservation of the jet axial and transverse momentum as
the jet is turned into the downstream direction by the boundary layer
flow (Campbell and Schetz 1973 give a very comprehensive and excellent
treatment of the equations governing a jet in cross flow). Profile 6
shows the jet lifted from the surface due to the 30 degree injection
angle.
47
The velocity profiles from Figure 3.23 have been spanwlse-averaged
using a Simpson’s rule type of quadrature, and the averaged velocity pro-
file is plotted in Figure 3.24. Shown also in the figure is a one-sixth
power velocity profile. Comparison of the two profiles shows the large
momentum deficit created by the discrete hole injection process. From
the spanwise-averaged velocity profile a shear stress profile was ob-
tained and is plotted in Figure 3.25. From the spanwlse-averaged ve-
locity profile and shear stress profile, a mixing-length distribution
was computed and it is plotted in Figure 3.26. The mixing-length pro-
file will be used in Chapter 4 to deduce the general form of an augmented
mixing-length expression. Details of the computing equations for the
shear stress profile and mixing-length profile are given in Appendix VI.
Temperature profiles for 0 = 1.00 (injectant temperature equal to
wall temperature) are shown in Figure 3.27. The presence of the jet can
be seen in profile 6. Profiles 1 and 11 show a large enthalpy excess
over a three-hole-diaraeter region above the surface. A similar set of
profiles were taken for 6 = 0.16 (injectant temperature about equal to
mainstream temperature), and they are shown in Figure 3.28. Again pro-
file 6 shows the presence of the mainstream-temperature fluid. In pro-
files 1 and 11 the presence of the "sink-type" injectant is not detected.
The temperature profiles for 0=1 and 0 = 0.16 have been spanwise-
averaged, and they are plotted in Figures 3.29 and 3.30 respectively.
Table 3.3 summarizes the momentum and enthalpy thickness Reynolds
numbers for the velocity and temperature profiles of Figures 3.23, 3.27,
and 3.28 (from tabulations in Appendix II). Also shown in the table are:
(1) ERe/11 , the arithmetic-averaged Reynolds numbers for the 11 pro-
files; (2) the Re values for the spanwise-averaged velocity and tem-
perature profiles of Figures 3.24, 3.29, and 3.30; and (3) the Re ^2
values computed by integration of the data in Figure 3.3 using the en-
ergy integral equation (2.9). The quantities referred to in (1) and (2)
are almost identical. The comparison between (2) and (3) shows that the
calculated (using experimental Stanton numbers) agree with the
spanwise-averaged Re ^2 within five percent.
48
Table 3.3
Momentum and enthalpy thickness Reynolds numbers
for the velocity and temperature profiles in Figures 3.23 through 3.30
Profile
ReA2(6 - 1.00)
Re^2^® “ 0.16)
1
6833
10,259
3898
2
6759
8,861
3924
3
6181
8,137
3920
4
5769
8,341
3991
5
6654
9,920
3910
6
6814
9,642
3409
7
7734
10,138
4001
8
7051
9,070
4296
9
6381
8,617
4181
10
6720
9,158
4158
11
7255
9,490
4079
ZRe/ll
6741
9,240
3979
Spanwise-
averaged
profile
6792
9,200
3978
Data
reduction
program
(midpoint
plate 11)
—
8,734
4052
49
Figure 3.1 Upstream velocity profile for Initially high *
heated starting length runs (see Section 3.3.1)
50
Figure 3*2 Upstream temperature profile for initially high ' Re‘g2 V
starting length runs (see Section 3.3.1)
P/D =5
Re^j “2700
Uoo —16.8 m/s
RUN M d
O 092874 0
□ 100174 0.39 0
m 100374 0.38 I
versus enthalpy thickness Reynolds number
lo' 2 5 10^ 2 5 10® 2
Figure 3.5 Upstream velocity profiles (P/D = 5, 10) for initially high
Reg2 t unheated starting length runs (see Section 3.3.2)
5
P/D =5
Figure 3.6 Stanton number data (P/D * 5) versus non-dimensional distance along surface for
Initial conditions in Figure 3.5, to study effects of blowing ratio
Uoo 16.8 m/s
RUN
M
o
073 1 74
0
▼
080334
0. 18
■
080174-2
0.37
♦
081174
0.52
A
081574-2
0.71
M
081974-2
0.85
♦
092474
1.21
Figure 3.6, replotted versus enthalpy thickness Reynolds number
Uoo —16,8 m/s
2
5
10 ^
^2
,6, replotted versus enthalpy thickness Reynolds number
16.8 m/s
^vo =OI3m
I 2 I I 74 0
121474 0.39
12 1274-2 0.36
121674-i 0.78
12 1674-2 0.75
Figure 3.9 Stanton number data (P/D = 10) versus non-dimensional dis
tance along surface for initial conditions in Figure 3.5,
to study effects of change in hole spacing
P/D =5
Re;; =^1900
Og
Uoo ~ 9 8 nf^/s
RUN M
O 092074 0
□ 092274-1 0.39 0
■ 092274-2 0.35 1
o 090874 0 ♦
□ 091474 0.39 0
■ 091674 0.38 1
mre 3,16 Data for Figure 3.15, replotted versus enthalpy thickness Reynolds number
y (cm)
Figure 3.17 Upstream velocity profiles (P/D = 5, 10) for initially low Re52 * lieated
starting length runs (see Section 3.3.4)
StQ = 0.0292 R6 x“
^ A A ^ AAAA^^iA
5 □ □ n n rir-/Tirrn.
^ ^ □□□□□EDa
^ ^
P/D =5
Re. 520
■52
Re. ^490
Ag
U^ =^ll.7m/s
= 1.08 m
•s.
o
102274
0
□
103074-1
0.41
■ :
103074-2
0.40
A
102874
0.79
A
102974
0.72
Figure 3.19 Stanton number data (P/D = 5) versus non-dimensional
distance along surface for initial conditions in Fig
ures 3,17 and 3,18, to study effects of thin Initial
momentum boundary layer
Sto = 0.0292 Pr"^‘^Rex‘
O 120274 0
□ 12 I 074- ! 0.42
A 120574-i 0.81
1 ^ ^ I L_1
O 120274 0
■ 121074-2 0.37
4 120574-2 0.80
10) versus non-dimensional distance along surface
igures 3.17 and 3.18, to study effetts of change
O .2 .4 .6 .8 1.0
U/U«
Figure 3.24 Velocity profile obtained by spanwise-averaging the
profiles in Figure 3.23
0 .2 .4 .6 .8 i.O
y/S
Figure 3.25 Shear stress profile obtained using the spanwise-
averaged velocity profile
73
Figure 3.26 Mixing- length profile obtained using the shear stress
profile and the spanwise- averaged velocity profile
Figure 3.27 Temperature profiles d
0 = 1.00 (see Figures
initial conditions)
75
iwnstream of ninth blowing row,
3 . 1 and 3 . 2 for boundary layer
Figure 3.28 Temperature profiles downstre^ of ninth blowing row,
6 = 0.16 (see Figures 3.1 and 3.2 for boundary layer
initial conditions)
76
y (cm)
5j
SPANWISE-
AVERAGED
TEMPERATURE
PROFILE
0 = 1.00
y (cm)
.2 .4 - .6 .8
T = (T-T„)/(To-T„)
Figure 3.29 Temperature profile obtained by apanwise-averaging
, the profiles in Figure 3.27, 6 = 1.00
SPANWISE-
AVE RAGED
TEMPERATURE
PROFILE
0 = 0.16
y (cm)
T = (T-T„)/(To“T„)
Figure 3.30 Temperature profile obtained by spanwise-averaging
the profiles in Figure 3.28, 0 =* 0.16
Chapter 4
ANALYSIS OF THE DATA
4.1 Effects of Full-Coverage Film Cooling on Stanton Nijmber
The heat transfer data have been presented in some detail in the
previous chapter. The purpose of this section of Chapter 4 is to sum-
marize the effects of injectant temperature and blowing ratio, upstream
initial conditions, and hole spacing on Stanton number.
4.1.1 Injectant Temperature and Blowing Ratio
One of the important factors in heat transfer with full-
coverage film cooling is the injectant temperature level, T^ , compared
with the surface and mainstream temperatures. Because of the linearity
of the governing energy equation for small temperature differences, the
heat transfer is a linear function of • Thus, the acquisition of
Stanton number data for two injectant temperatures (all other parameters
fixed) provided sufficient information to define the Stanton number as
a continuous function of T^ . For the steady state heat transfer tests
described herein, the injectant temperatures were ~ (6 = 0) and
T 2 = T^ (0 = 1) . For gas turbine applications T 2 < T^ < T^ , resulting
in a 0 parameter slightly larger than unity (Colladay 1972) . Therefore
the 0=1 data trends described in Chapter 3 should be indicative of
the Stanton number behavior on a full-coverage turbine blade.
While Stanton number is a simple function of 0 , it is a very com-
plex function of blowing ratio. Figure 4.1 shows Stanton numbers from
plate 11, Figure 3.6, plotted versus blowing ratio. The data exhibit a
nonlinear dependence of St on M for P/D = 5 . Also shown in Figure
4.1 are predicted Stanton numbers for a typical 0 operating condition
to demonstrate the superposition principle. The predicted Stanton num-
ber decreases to a minimum at M = 0.4 and then rises as M increases.
This minimum in St for a t 3 rpical 0 operating condition is clearly
seen in the 0=1 data. This minimum appears to be independent of up-
stream initial conditions. For example the data in Section 3.3.4 (thin
initial boundary layer) shows M ~ 0.4 produces a lower St (0 = 1) than
does the M - 0.8 data, for both P/D = 5 and 10 .
78
The drop in Stanton number for low M and 0=1 is similar to
that found in transpiration cooling, but not as pronounced. With both
cooling schemes the heat transfer is reduced due to addition of wall
temperature fluid which significantly alters the temperature profile in
the near-wall region. However, the cooling effect is diminished with
full-coverage cooling because of increased turbulent transport. The
spanwise velocity profiles indicate the full-coverage jets affect the
transport over a range from the wall to at least two hole diameters
above the wall, whereas with transpiration only the sublayer is affected.
Thus, for an equivalent wall mass flux of coolant (equal F) , the Stanton
number with film cooling will be higher.
The change in Stanton number with M for M > 0.4 suggests the
film cooling jets are delivering the coolant further out into the bound-
ary layer. This increased penetration distance has a two-pronged effect.
By depositing the coolant farther away from the surface, the coolant must
be convccted or diffused back into the near-wall region in order to re-
duce the wall heat transfer. During this process the coolant entrains
boundary layer fluid, and in particular, near-mainstream temperature
fluid, and equilibration with the entrained fluid severely reduces the
effectiveness of the coolant. The second major effect of increased pene-
tration is Increased turbulence production. The resulting increased
turbulent transport in the outer layer may enhance the coolant diffusion
back to the surface, but it also enhances the jet entrainment process
which "dilutes" the coolant.
In the recovery region the Stanton number response for 6=1 has
three distinct patterns. For low blowing ratio (M < 0.4) the boundary
layer immediately begins to recover in a manner similar to the region
downstream of a transpiration section. For M = 0.4 the recovery region
heat transfer becomes a constant, at least for the recovery region of
these experiments (about 60 hole diameters). For M > 0.4 the Stanton
number continues to decrease throughout the recovery region.
The recovery region response suggests that it may be possible to
use an interrupted hole array pattern for turbine blade cooling. If the
thermal boundary layer can be "pumped up" with coolant from several rows
79
of holes, then downstream of those rows the Stanton number will be de-
layed in rising. (This conclusion is based on P/D = 5 data only, and
for a very low mainstream turbulence level).
Presumably what happens in the recovery region is that the thermal
boundary layer is spatially "frozen" because there no longer exists a
mechanism for fast diffusion of the "pumped up" temperature profile
(see Figure 3.24 for a typical 0=1 temperature profile). The pro-
file restoration must come from turbulent mixing, but its predominant
source will be wall-generated turbulence. In effect, a new momentum
boundary layer begins in the recovery region, and until it engulfs the
major part of the existing thermal boundary layer, the Stanton number
will be depressed.
4.1.2 Upstream Initial Conditions
The initial conditions of the turbulent boundary layer were
systematically varied to obtain data for developing integral correla-
tions and for testing differential prediction models. Figure 4.2 shows
all the data for M = 0.4 and P/D = 5 , replotted as St(6)/St ver-
o
sus the downstream distance, x , where St is Stanton number for
o
M = 0 and the same upstream initial conditions as St(0) .
In Figure 4.2 the Stanton number ratios for 9=1 drop below
unity in a fairly tight band for both the blowing and recovery region
(note there is no apparent explanation of why the Reg 2 - 2700 unheated
starting length data should be low, when corresponding data at Reg 2 "
1900 and 4700 are within the band). This tight grouping for
6=1 suggests there is, at most, a slight effect of on Stanton
number. For example, the Reg 2 ~ 1900 and 520 data, both with about
the same but much different initial boundary layer thicknesses,
have slightly higher Stanton number ratios than data with higher main-
stream velocities. This velocity dependence is introduced into the
data correlation in Section 4.2 in terms of a hole-diameter Reynolds
number, Re^ = DU /v .
Also shown in Figure 4.2 are Stanton number ratios for 6=0.
The low and high Reg 2 data with heated starting length rise in the
initial blowing region whereas the high Red2 data without a heated
80
starting length do not. This is a thermal boundary layer effect. In-
jecting 0=0 fluid does not directly contribute to the growth of
Re^2 t so until the thermal boundary layer grows beyond the penetration
height of the jets» the Stanton number is only marginally different from
St ,
o
4; 1.3 Hole Spacing
Stanton numbers were obtained for P/D = 5 and 10 and visual
comparison of these data in Chapter 3 revealed a much diminished effect
for the same M with the wider hole spacing. The comparison is more
meaningful when the data are compared at equal F , which implies equal
mass flux of coolant Injected over a given surface area. This comparison
will be made in the next section.
4. 2 Correlation of the Stanton Number Data
One method of evaluating film-cooling performance is to evaluate
surface heat flux with and without film cooling, q”(0)/q" > at the same
location on the surface. Because both heat fluxes are defined using the
same convective rate equation, the film-cooling performance can be sim-
plified to evaluation of h(0)/h or St(0)/St . The St(0) informa-
o o
tlon can be obtained by applying superposition to correlations of the
fundamental Stanton number data sets at 0=0 and 0=1.
The data for 0*1 were correlated based on a Couette flow analy-
sis developed by Choe et al. (1976),
St(0 - 1)
St
o
£n(l +
(4,1)
where B^ is the blowing parameter, defined as B^ = F/St(0 = 1), and
Is a function that is unity for transpiration cooling, and greater
than unity for full-coverage film cooling. Thus, Is a measure of
departure from the Ideal case of transpiration cooling.
Figure 4.3 shows all data for 6 = 1 plotted as 4) versus F ■
0 2
Re_* , The solid line for P/D - 5 and the dashed line for P/D = 10
D,00 '
are best-fit lines for the data. Both lines change slope at an F cor-
81
responding to M ~ 0.4 . As discussed In Chapter 3, this blowing ratio
appears to be the highest value for which the cooling jets remain atr
tached, to the surface (at least for the P/D = 5 data).
-The mainstream velocity effect mentioned In Section 4.1.2 is re-'
0 2
fleeted In the F • product. The 0.2 power Indicates a small ef-
sfiBct on Stanton number ratio for changes In . It Is presumed that
Re. Is the correct correlating parameter; no tests were conducted
'.with changes In hole diameter to verify It. However, the trend In the
functional dependence for ^ Is In the right direction, l.e., as
D becomes smaller, <j> becomes smaller for the same F , and In the
limit as It approaches zero, approaches unity, which Is transpiration
pooling.
The effect of changing the pltch-to-dlameter ratio Is also seen In
Figure 4.3. For a given blowing fraction, the (P value Increases, In-
dicating even less effective surface protection, l.e., higher heat trans-
fer coefficients. This Is not surprising, since, to have equal F
(mass flux of coolant), as F/D Increases, M must also Increase, re-
stilting In greater jet penetration and Increased turbulent mixing.
Correlations of the 6 1.0 data for P/D = 5 and M > 0.4 are
as follows :
St
0.5 + 23.2 F • Re^’^
' ' ' St
o
Re*
D,ooJ
(4.2)
or, in R®A 2 coordinates (following Whitten, Kays, and Moffat 1967)
The values for St In equation (4.2) or (4.3) are
o
smooth flat plate values, as recommended by Kays (1966),
The data summary sheets In Appendix I give values for (j)
tlon used to generate St^ values.
the typical
for example,
and the equa-
82
I
For 6=0, the Stanton number data could be correlated as a func-
tion of Re_ for those data which reached an asymptotic state, inde-
D |00
pendent of the number of rows of holes upstream. Correlation of the data
was particularly troublesome because of insufficient asymptote data.
Stanton numbers for M < 0.4 at P/D = 5 failed to reach an asymptote
because of the unheated starting length initial condition. Stantoii num-
ibers for P/D = 10 did not reach an asymptote because of insufficient
test surface length; l.e., only six rows of holes were available when the
test section was reconfigured.
For M > 0.4 and initial Rex^ - 500 (Re = 7900) , the correlating
equation for P/D = 5 data is
St(0 = 0) = 0.0132 F°‘^^ ;(4,4)
. .. r
For Refi« ~ 2700 (Re_ = 11,200) and P/D = 5 the correlating equation is
Z D 900
St(0 = 0) = 0.0112 F^’^^ (4.5)^^
4.3 Development of a Prediction Model
The overall goal of the full-coverage fllm-cpoling research at StJUi-
ford is to develop a prediction method to aid in design of full-coverage
turbine blades. Three types of methods were considered:' (1) integral
analysis, (2) two-dimensional differential analysis, and (3) three-dimen-
sional differential analysis. A differential type of analysis was chosen
primarily because of its provision for a greater flexibility in turbulence
modeling.
In choosing between using a two-dimensional differential analysis
(coupled with simple empirical models for the film-cooling process) and
a three-dimensional analysis (perhaps the only "true" analysis), the fol-
lowing were considered: the computation scheme had to have a relatively
short execution time to make it attractive as a "design tool", and the
scheme had to have a relatively small computer core requirement.' Based
on these criteria, a two-dimensional scheme was pursued.
The differential method that was developed consisted of the two-
dimensional boundary layer program, STAN5, with added routines to model- '
the injection process and turbulence augmentation. Flow over the full-
83
coverage surface was considered to be describable by boundary layer equa-
tions (see Herring 1975 or Choe et al. 1976 for a discussion of the
applicability of these equations). The program solves these equations,
inarching in the streamwise direction. Fluid Is injected into the bound-
ary layer by stopping the program when a row of holes is encountered and
dividing the injected fluid among the stre^ tubes between the wall and
some "jet penetration point". The jet-boundary layer interaction is
modeled by augmenting the Prandtl mixing-length. Two "constants" are re-
quired, in addition to the accepted constants for predicting boundary
layer flow over a flat, slightly rough plate
The boundary layer equations being solved are those described in the
STANS documentation report (Crawford and Kays 1975) for flow over a flat
surface
l^(PU) + l^(PV) « 0 ' (4.6)
"®c dx
l-(u ^)
9y^^eff 9y^
(4.8)
* 2 ,
where I = I + U /2g^J . The effective viscosity and effective Prandtl
number are defined in terms of an eddy viscosity and turbulent Prandtl
number ,
^eff “ + V
where is the turbulent viscosity, is the turbulent conductivity,
and c is the specific heat.
84
I
The eddy dlffusivity for momentum is modeled by the Prandtl mixing-
length
'M
iy.
9y
(4.11)
The mlxihg-length distribution will be described in Section 4.3.2.
The turbulent Prandtl number, Pr^ , is presumed to follow the flat
plate, variation described in Crawford and Kays (1975). The Pr^ distri-
bution, is for air; it is 1.72 at the wall and drops to 0.86 in the outer
region..
Boundary conditions for the "two-dimensional" flow equations are
U(x,0) =0 (4.12a)
V(x,0) = 0 (4.12b)
and
Lim U(x,y)
y*oo
(constant)
(4.12c)
I*(K.O)
I (constant)
o
Lim I
yXXJ
(x.y)
(constant)
(4.12d)
(4.12e)
4.3.1 Injection Model
In constructing a model for the film-cooling injection pro-
cess, consideration was made of the physical process occurring when the
jets enter the boundary layer. For low M the jets do not penetrate;
they are immediately "knocked over" by drag forces on the emerging jets
(primarily pressure forces from the retarded boundary layer flow upstream
of the jets). For higher M the jets emerge from the surface and are
turned into the downstream direction by pressure and shear forces which
overcome the jets* resistance to direction change. As each emerging jet
moves through the boundary layer, the shear layer at the injectant-
boundary layer interface promotes entrainment of boundary layer fluid
85
into the jet. This spreads the jet and slows it; eventually the inject-
ant becomes diffused into the existing boundary layer fluid.
,, The injection process and the entrainment-diffusion. process are
modeled together. As a jet passes through the stream tubes that comprise
the boundary layer, drag forces arising due to the jet/cross-stream inter-
action are presumed to "tear off" some of the injectant. The injectant
that is shed into a given stream tube is then accelerated by the drag
forces. ’^This process is depicted below. Shedding continues into suc-
cessive stream tubes until the amount shed equals the mass flow of the
injectant. The distance where shedding is complete is called the pene-
tration distance.
Equations that describe the model are obtained from one-dimensional
mass, momentum, and thermal energy balances on the element of injectant
bounded between two stream surfaces. For flow between these surfaces.
m = m . , + 6m (4.13)
new old
where m is the flow rate upstream and 6m is the injectant that is
old
shed (on a rate basis) ., From a moment;um balance consideration,
86
’ (*old +
6m) U
new
m - ,U , j + 6mU«cosa
old old 2
(4.14)
where is the mass-averaged velocity of the upstream fluid and . U^,
is the velocity of the injectant. The velocity is assumed not to
vary with y , This is the simplest way to preserve overall momentum .
within the boundary layer (l.e. » Z6mU2 ■ ™jet^2 * where U2 *
The drag forces that "tear-off” the injectant are assumed to accel-
erate 6m from its initial velocity up to the new stream-tube velocityi
g^F - 5®(U^ew “
The drag forces can be defined in terms of a drag coefficient for con-
venience,
("old
where is the cross-sectional, area of the jet, (D • 5y)/sina for a.
stream tube that is 6y in width (proportional to , . -
By introducing the definition * where P is
the distance between adjacent jets, and combining with the above equations,
the ratio of the mass shed from the coolant jet to the existing mass be-
tween the stream tubes (on a rate basis) can be written as
' ' 6m
■ m , ,
old
A mass-averaged velocity
( 4 . 14 ):
IF
new
From energy balance considerations.
2(P/D)
slna
V "old /
(4.17)
ratio can be formed by rearranging equation
(
L H.
“old/
(4.i8)
87
(4.19)
^new^*old +
m 1 , + <5ml, ^
old old j et
7 S
where I ^ , is the mass-averaged stagnation enthalpy of the upstream
old ^
fluid and I. is that of the injectant (assumed not to vary with y
jet
to satisfy overall energy conservation) . A mass-averaged enthalpy ratio
can be formed by rearranging equation (4.19):
(4.20)
In the prediction program, the Injection model, based on the analysis
given above, is contained in a subroutine, and it is invoked when a row of
holes is encountered. The empirical input is the mass shed ratio, defined
as
= DELMR (4.21)
“old
The DELMR expression is used in lieu of equation (4.17) for simplicity.
With this input "constant", the routine processes each flow tube from
the wall outward. The velocities are adjusted according to equation
(4.18) to conserve momentum. The stagnation enthalpies are adjusted ac-
cording to equation (4.20). The injection process is terminated when
= P2^2 ^ ^ DELMR • (4.22)
Note the introduction of P to put the flow rate on a per-unit depth
basis (consistent with the dimensions of ijj ). The y location where
flow distribution is completed is PD , the penetration distance. This
calculated distance is a significant variable in the augmented turbulent
mixing model, for it is at this point that the increased mixing has its
maximum .
88
The eddy diffusivlty for momentum Is modeled by the Prandtl
mixing- length. To account for the jet /cross-stream interaction the mix-
ing-length is augmented, using a variation of a model first described by
Choe et al. (1976).
(4.23)
where the "2-d” subscript refers to the two-dimensional mixing-length,
and the "a" subscript denotes a departure due to discrete-hole Injection.
The functional form for the (il/6) expression was determined from the
computed mixing-length distribution given in Section 3,4 . The functional
form is depicted below.
I
U /8)
max, a
The curve represents a departure from the two-dimensional mixing-
length value, with a mcnclmum departure, ,(^/6) , located -at PD ,
■ : , * m3X } 3
the penetration distance from the wall, as determined by the injection
model. . - ' . -
The two-dimensional mixing-length is
KyD
Vd ■
Ky < X6
Ky > X6
(4.24)
where D is the Van Driest damping function,
D ■ 1 - exp (-y'*'/A^) (4.25)
In the predictions k “ 0.41 , X = 0.085 , and A = 22 in the blowing
region for P/D * 5 (to account for surface roughness) and = 25 in
the smooth, flat-plate recovery region.
The augmented mixing-length is given by
where
(4.26)
K
O
. W6)
(PD/6)
(4.27)
In the above equations, PD is the penetration distance of the injectant,
determined from the Injection model. The boundary layer thickness (actu^
ally the ninty-nihe percent point) is 6 . The maximum mixing- length
augmentation, occurring at y * PD , is (^/<5) . This is the second
t&£LX I d.
input "constant" for the prediction scheme. Note that equation (4.26)
contains the Van Driest damping function merely for programming conven-
ience; the damping function approaches unity well before there is an ap-
preciable contribution from the other terms in equation (4.26).
90
One of the most perplexing problems associated. with .the prediction
scheme was in the initial blowing region. and initial recovery region. .
In the initial blowing region a"^ changes from a smooth plate value to
a"*" for the rough, discrete-hole plate, and goes from zero to its
maximum value, proportional to (^/5) . The reverse transition oc-
I Si
curs in the initial recovery region.
The A^ transition was handled by invoking a' first order lag equa-
tion similar to that described by Crawford and Kays (1975),
dA
eff
dx
(4.28)
where is ihe effective Van Driest damping constant, A is the
asymptotic value (22 for the rough, P/D = 5 surface ; 25 for the smooth
recovery region), and C = 6000 . Thus a"^ starts out at 25, drops-
toward 22 when the first row of holes is encountered, and then returns ; to
25 in the downstream recovery region; With this lag equation, the St^
data were adequately predicted with no initial region problems.
The transition was also handled by solving an equation like
(4.28) for (^-/6) . For the initial blowing region, the asymp-
tote of the equation is , and in the initial recovery regiou,
I110X ^ 3 l
the asymptote is zero. To simulate the beginning of the transition, the
initial (^/< 5 ) was given a step change. This method is described
ni0x y 0
by Choe et al. (1976) for abrupt changes in transpiration, and it is
depicted as shown below.
91
The step-change constants CLl and CL2 were 0,3 for predictions of
low M data. The CLl value was changed to 1.0 in attempt $ to model
the high M. data. Based upon the predictions, it can be concluded that
the initial region modeling was, at best, marginal. Fortunately, though,
values for the step-change constants do not affect the Stanton number
predictions in the region far downstream of the step location,
4. 4 Numerical Prediction of the Data
Predictions of most of the P/D = 5 data have been made to assess
the model outlined in the previous section. The constants DELMR and
(£/6) that successfully predicted the data are shown in Figure 4.4,
plotted versus the blowing ratio. In the figure, DELMR decreases as M
increases, resulting in increased penetration distance, and (^-/6)
max, a
is seen to increase as M increases, indicating more intense turbulent
mixing. The most interesting data point for these "computer-experiment"
constants is at M = 0.4 . Recall there were five data runs at this
blowing ratio (summarized in Figure 4.4). Four of the five runs were
satisfactorily predicted with the same constants. The fifth run, with a
very thin initial boundary layer, required a slightly higher value of
(i^/6) , indicating a slightly higher turbulence level for this
^ Si
initial condition.
The first data set to be predicted is that discussed in Section 3.3.1
(thick initial boundary layer with heated starting length). Figure 4,5
shows Stanton number predictions for M = 0 and 0 = 0 , 1 at M = 0.4 .
The 0=0 prediction spikes upward when mainstream - temperature fluid
is injected into the boundary layer. Similarly, the prediction spikes
downward when wall- temperature fluid is Injected, Predicted velocity and
temperature profiles are shown in Figures 4.6 through 4.8. They are
compared to the spanwise-average profiles discussed in Section 3.4 .
To test the film-cooling model, the predictions described in the
preceding paragraph were carried out for 24 rows of holes. Shown in
Figure 4.9 are the finite-difference data points for prediction of 12 and
24 rows of holes. Past the first 12 rows only the average Stanton numbers
per row are plotted. For 9=0, the predictions continue to exhibit
an asymptotic behavior; for 6=1 the predictions continue to decrease,
but at a slower rate, as if it were also approaching an asymptote.
92
The second data set to be predicted Is the P/D « 5 data discussed
in Section 3.3.2 (thick Initial boundary layer with unheated starting
length).' Figures 4.10 through 4.13 shows the predictions. The two weak
features' of the predictions are the initial blowing region for 0 “ 0
and the recovery region for 6=1.
The third data set to be predicted is the data discussed in Section
3.3.3 (thick initial boundary layer with change in mainstream velocity).
Figures 4.14 and 4.15. show the predictions. The last data to be predicted
is the M.« 0. 4 blowing ratio data at P/D = 5 , discussed in Section
3.3.4 (thin initial boundary layer with heated starting length). Figure
4.16 shows the prediction.
1
Figure 4.1 Prediction of St for 0-1.3 by applying superposition
to fundamental data sets, Figures 3,6 (plate 11)
9
95
DCLMR
Figure 4.4 Two constants used In prediction model
97
'0.99 i max,
5
Figure 4.6 Prediction of the
Figure 3.24
T
99
O STAN5
■ EXPERIMENT
24 ROWS (average value)
O G Q. O O O. Q O Q O O
12 ROWS
24 ROWS (overage value)
.6
X (m)
Figurt 4.9 Extension of the M » 0.4 prediction (Figure 4.5) to 24 rows of holes to
show stable behavior of injection model
figure 4.11 Prediction of the M ~ 0,4 data from figure!. 6
103
St
P/D = 5
2700 (ini.)
Uqo = 16.8 m/s
RUN M e
O 080574 0.58 0
♦ 08 1174 0.52 i
10
-3
8
10 ®
2
Re,
Figure 4.12 Prediction of the M = 0.6 data from Figure 3.6
104
Chapter 5
SUMMARY AND RECOMMENDATIONS
An experimental and analytical Investigation of heat transfer to
the boundary layer over a full-coverage, film-cooled surface has been
carried out. Injection was from an array of staggered holes with hole
spaclng-tb-hole diameter ratios of 5 and 10. The holes were angled 30
degrees to the surf ace ; In . the downstream direction. In summary,
1. Experimental Stant oh number data have been acquired, using two
temperatures at each blowing ratio to build two fundamental data
sets. The data are defined using a wall temperature-to-maln-
stream temperature driving potential to permit direct comparison
of wall heat fluxes, with and without film cooling, to describe
fllm-coollng performance. Superposition can be applied to the
two fundamental data sets to obtain Stanton number as a contin-
uous function of Injectant temperature.
i ■' -
2. When the Injectant temperature., equals plate temperature* the
lowest Stanton number, ^s produced for a blowing ratio (injectant
veloclty-to-^alnstream velocity) of about 0.4 . Higher ratios
resulted In higher Stanton numbers. The data trend Indicated
that for ratios above 1.5 the Stanton number could be larger
than that without film cooling.
3. The major effects on Stanton number of changing either the up-
stream momentum thickness or the ratio of thermal-to-momentum
thickness are confined to the Initial blowing rows. The data
showed a slight dependence upon changes In mainstream velocity.
4. Comparison of the data for the two hole spaclngs Indicates that
a wider hole spacing (10 hole diameters) produces less effect on
Stanton number, for the same value of blowing ratio.
5. The data for Injectant temperature equal to plate temperature
were successfully correlated using the same Couette flow varia-
bles used to correlate transpiration cooling data.
109
6, The recovery region, 60 hole diameters downstream of the last
blowing row, had two distinct data trends for the case of in-
jectant temperature equal to plate temperature. For low veloc-
ity ratios the Stanton number immediately began to recover to-
ward the corresponding unblown value, while for high velocity
ratios the Stanton number either remained constant or dropped
throughout the recovery region. This latter behavior suggests
investigating an interrupted hole pattern with, say, five to ten
rows of holes followed by a recovery region, before the next ar-
ray begins.
7. A differential prediction model was developed to predict the
experimental data. The method utilizes a two-dimensional bound-
ary layer program with routines to model the injection process
and turbulence augmentation. The program marches in the stream-
wise direction and, when a row of holes is encountered, stops
and injects fluid into the boundary layer. The turbulence level
is modeled by algebraically augmenting the mixing- length, with
the augmentation keyed to a penetration distance for the Inject-
ant .
The work described in this report represents the second of three
phases of experimental heat transfer investigations into full-coverage,
film-cooled boundary layers at Stanford: first was normal-hole injec-
tion; the second was the slant- hole injection, and the third will be
with compound-angled hole injection. Presently an experimental
investigation of the slant-hole flow field is being carried out, and
the compound- angled hole test section is being constructed. It is
recommended that:
1. A higher-level turbulence closure model should be investigated
for use in the turbulence augmentation model of the prediction
program described herein. The logical choice would be a turbu-
lence kinetic energy model. This is being pursued.
2. The effects of high mainstream turbulence level on heat transfer
should be investigated. The importance of this effect may be
110
confined to the recovery region, and to. the results described
in point 6 of the summary above. The high turbulence level may
promote a much faster recovery to unblown Stanton number condi-
tions. .
A preliminary investigation should be carried out regarding
availability of ' three-dimensional boundary layer programs for
modification to predict the full-coverage data. This recom-
mendation is made in light of the much-improved cbmputer exe-
cution time and core availability of the new generation of com-
puters at Stanford. Such machines will be available to industry
in the coming decade; thus it seems a justifiable course to
pursue.
Ill
Appendix I
STANTON NUMBER DATA
Contained In this appendix Is a numerical tabulation of the Stanton
number data. Initial velocity and temperature profiles precede the data*
and the sequence of data follows the discussions In Sections 3.3.1
through 3.3.4. For the Stanton number data at each blowing ratio the
experimental data at 6 ~ 1 and 6 0 are given first, followed by a
sheet with the superposition-adjusted data to values at 6 » 0, 1 •
Nomenclature
CF/2 c^/2 , friction coefficient
CP c , specific heat
DEL velocity or thermal boundary layer thickness (see DEL99 or
DELT99)
DELI 6^ , displacement thickness
DEL2 6^ , momentum thickness
DEL99 velocity boundary layer thickness
DELT99 thermal boundary layer thickness
DREEN uncertainty in Re^2
DST uncertainty In St
DTM uncertainty in 0
ETA
{1 - St(0 = 1)}/St(0
F
blowing fraction
F-COL
F at 0=0
F-HOT
F at 6=1
H velocity shape factor
LOGB (j) function in 6 = 1 data correlation
112
M
PORT
PR
RE DEL2
REENTH
REH
REM
REX
RHO
ST
STCR
STHR
T
T2
TADS
TEAR
THETA
TINF
TO
TPLATE
U
U+
UINF
Vise
XLOC
blowing parameter
topwall location where profile is obtained
Pr , Prandtl number
Re ^2 » enthalpy thickness Reynolds number
Re^^ » momentum thickness Reynolds number
Re^ , x-Reynolds number
density
Stanton number
St(0 = 0)/St , Note, St is defined at bottom of each
' o o
summary data sheet.
St(0 =* i)/st^
recovery temperature of temperature probe
T 2 I secondary air temperature
T^ , r , temperature to define Stanton number
(T^-T) / (T^“T^) (or one minus that quantity in the second tab~
ulated data column)
0 , temperature parameter
mainstream static temperature
T^ , plate temperature
velocity
11+ , non-dimensional velocity
, mainstream velocity
V , kinematic viscosity
X , distance from nozzle exit to probe tip
113
xvo
>
Y
Y+
distance from nozzle exit to virtual origin, turbulent
VO
boundary layer
y , distance normal to surface
y , non-dlmenslonal y distance
Note: Some of the entries In the Stanton nimiber data summary sheets are
boxed In. These data points deviate substantially from the data
trend of their surrounding points. Therefore, they were not plot-
ted as tabulated, but adjusted and then plotted.
114
115
RUN 092874 VELOCnV AND TEMPcKATURE PROFRcS
REX
-
0.1178 7F 07
REM =
2(>b3.
REH
= 1844.
XVO
20.98
CP.
DEL2 =
0.241
CM.
DEH2
= 0.167
CM.
UINF
16.83
M/S
DEL99=
2.04iJ
CM.
DELT99
= 1-894
CM.
Vise
-
0. 15247E-04
K2/S
DELL =
0.3 6Q
CM.
UINF
= 16.84
M/S
PORT
=
19
H
1
V I SC
= 0.15263E-04
M2/S
XLOC
=
127. 76
CM.
CF/2 =
0.16/94E-02
TINF
= . 21.96
DEG C
TPLATE
= 36,46
DEG C
Y(CM. )
Y/DFL
U(M/S>
U/LINF
Y +
U +
YICM. 1
T(DEG C)
TBAR
TBAR
0.025
0.012
7,31
C.434
11
1 0 *o 0
0.01o5
33,33
0.218
0.782
0.028
0.014
7.56
0.449
12.6
10.96
0.0190
32.24
0,293
0,707
0.030
0.015
7,79
0.463
13,8
11.29
0.0216
31.51
0.344
0.656
0.036
0.017
8.21
C.488
16.1
11.91
0.0241
31,09
0.373
0,62 7
0.04 3
0.021
8.62
C.512
19.5
12. 5U
0.0292
30.21
0,434
0.566
0.053
0.026
9.15
C.544
24.1
13.26
0.0368
29.45
0.487
0.513
0.066
0.032
9.51
0.565
29.9
13. 79
0.0470
28.63
0.544
0.456
0.081
0.040
9.75
0.579
36.8
14.14
0. 0597
28.02
0. 587
0.413
0.099
0.048
10.06
C.598
44.8
14.59
U.0775
27.45
0.627
0.373
0.119
0.058
10.31
0.612
5^. .0
1 4 . 9h
0,097b
27.08
0,653
0.347
0. 142
0.070
10.58
C.629
64.3
15.35
0.1232
26.73
0.677
0,323
0.168
0.C82
10.73
C.637
75 , d
15.55
0.1537
26.41
0.699
0.301
0. 198
0.097
11.0 3
C.656
89.6
16.00
0.1892
26.07
0. 722
0.278
0.234
0.114
11.27
C.670
105. 7
16.34
0,2299
25,82
0.740
0.260
0,274
0.134
11.56
C.687
124. i
lo. to
0.2 75b
25.51
0.762
0.230
0. 320
0.156
11.87
C.705
144,8
17.21
0.3264
25.27
0. 778
0.222
0.371
0.181
12.07
0.717
167.7
17,51
0.3d99
24.97
0. 799
0.201
0.432
0.211
12,38
C.735
195.3
17,94
0.4661
24.71
0.817
0,183
0.503
0,246
12.73
C.756
2.17.5
18.46
U,5o01
24.40
0,839
0.16 1
0. 592
0.289
13.08
C.777
267.7
18.97
0.6871
24.02
0.865
0.135
0.693
0.339
13.47
C.800
313.7
19.53
0.U141
23.68
0. 888
0.U2
0.818
0.400
13.86
C.823
370.0
20.09
0.9411
23,41
0.908
0,092
0.970
0.474
14.39
C.855
43o.9
20 . 0 7
l.Obbl
23.17
0.924
0.076
1. 123
0. 549
14.84
C.682
507 .d
21.5.1
1. l'»51
22.96
0.939
0. 06 1
1.275
0.623
15.23
C.905
576 • d
22,08
1.3221
22.78
0.952
0.048
1.427
0.698
15,60
C.932
645 • 7
22.73
1,4491
22.60
0.964
0.036
1.580
0.7 72
15.98
C.950
714,7
23.17
1.5761
22.47
0.973
0.02 7
1,732
0.847
16,30
C.969
7dJ .6
23.64
1.7031
22.34
0.982
0.018
1,885
0.921
16.53
C.982
d52 , 5
1.8301
22.27
0.987
0.013
2.03 7
0,996
16.68
C.991
921,5
24.1b
i.9i;/l
22.20
0.992
0.008
2,139
1 .070
16.8 1
C.999
99J .4
2.0841
22.14
0.996
0,004
2. 342
1.145
16.83
l.OCO
1059.3
24.40
t.-ilU
22.11
0.998
0.002
2.336
22.09
l.OOO
0.000
2.465
22.08
1.000
0.000
f
116
ft’JN C92 874
DISCRETE HOLE RIG *** NAS-3-14336
STANTCN NUMBER DATA
TADB =
21.87
DEG C
UINF
=
16.81 M/S
TINF= 21.75
DEG C
RHQ =
1,187
KG/M3
VIS c
= 0.15
243E-04 M2/S
XVO= 21.0
CM
CP =
10 13.
J/KGK
PR=
0*716
2700HSLFP P/D =
= 5
PLATE
X
PEX
TO
REENTH
STANTON NO
DST
DREFN
ST(THEO)
RATIO
1
127. 8
0. 11776E
07
0il8684E
04
0.22298E-02
0.516E-04
28,
0.20 5 856 - 02
1. 083
2
132.8
0.12337E
07
26. 27
Oil9950E
C4
0-22897E-02
0.519E-04
28.
0.20395E-02
1.123
■a
137.9
0.128S7E
07
36.31
0121229E
04
0.22765E-02
0.517E-04
28.
0.202146-02
1.126
4
143.0
0.13457E
07
26.27
C*22495fc
04
0.22419E-02
0.517E-04
28.
0. 200436-02
1.119
5
148.1
0.14017F
07
36 .27
0i23750E
04
0.22392E-02
0.5176-04
28.
0.19880E-02
1.126
6
153.2
0. 14578E
07
26. 27
0*24998E
04
0.22167E-02
0.515E-04
28.
0.19725E-02
1.124
7
158.2
0. 15138E
07
36.25
0*2623 7E
04
0 .22067E-02
0.515E-04
26.
0.19577E-02
1.127
8
163.3
0.15698E
07
26. 25
Ci27462E
04
0.216366-02
0.513E-04
29.
0.19435E-02
1.113
9
168.4
0.16258E
07
36-27
Oi28666E
04
0.21344E-Q2
0.511E-04
29.
0. 19299 E-02
1.106
10
173.5
0.16819E
07
36.27
0*29854E
04
0.21079E-02
0.510E-04
29.
0.19169E-02
1.100
11
178.6
0.17379E
07
36. 25
Ci31029E
04
0.2C855E-02
0. 5096-04
29.
0.190 44 E-02
1.095
12
183.6
0.17939E
07
36.25
0132195E
04
O.2C774E-02
0.509E-04
29.
0.18923E-02
1.098
13
167.5
0.18 36 5E
07
26.23
0i33€57E
04
O.19420E-O2
0.6826-04
29.
0.18835E-02
1.032
14
190.1
0.13653E
07
26.29
0*33617E
04
0.19322E-02
0.6786-04
29.
0. 187766-02
1.029
15
192.7
0- 18942E
07
26.63
0i34l72fc
04
0.19113E-02
0.6816-04
29.
0.18718E-02
1.021
16
195.4
0. 19232E
07
■26.65
C.34722E
04
0.189 30E-02
0. 6666-04
29.
0.18662E-02
1.014
17
198.0
0. 19 52 2E
07
36. 67
0*35267E
04
0.188646-02
0.6666-04
29.
0.18606 E-02
1.014
18
200.6
O.1901OE
07
36.63
0A35812E
04
0.1E845E-02
0.6656-04
29.
0.18551E-02
1.016
19
203.2
C. 20099E
07
36. 57
0<*36354E
04
0.186616-02
0.650E-04
29.
0. IB498E-02
1.009
2C
205.8
0.20387E
0?
36. 71
0i36891E
04
0.18546E-02
0.6566-04
29.
0.18445 E-02
1.005
21
20 8.5
0.20676E
07
,36.61
Oi37428E
04
0.186056-02
0.6516-04
29.
0.1B393E-02
1.012
22
211.1
0.209646
07
26. 65
0*37966E
04
0. 18636E-02
0.6616-04
29.
0.18342E-02
1.016
23
213. 7
0c212S3E
07
36.61
Oi30<t97E
04
0 .181766-02
0.641E-04
29.
0.18292E-02
0.994
24
216.3
0.21543E
07
36.71
0i39025E
04
O.10344E-O2
0.6576-04
29.,
0.18243E-02
1.006
25
218.9
0. 213336
07
36.59
0-39552E
04
0 . 18166E-02
0.645E-04
29.
0.18194E-02
0.998
26
221.6
0.221216
07
36. 46
Ci40079E
04
0.18293E-02
0.6856-04
29.
0.18146E-02
1.008
27
224.2
0.2241 OE
07
35. 18
0140605E
04
0.18154E-02
0.591E-04
29.
0.18100E-02
1.003
28
226. E
0. 22698E
07
26.46
C*41 130E
04
0.181956-02
0.688E-04
29.
0.18053E-02
1.008
29
229.4
0.22987E
07
36.40
0141654E
04
0.180636-02
0.626E-04
29.
0.18008E-02
1.003
30
232.0
0.23275E
07
26.86
01421606
04
0.183646-02
0.665 E-04
29.
0-17963E-02
1.022
31
234.6
0.23564E
07
26.86
C1427C7E
04
0, ieillE-02
0.645E-04
30.
0.17919E-02
1.011
32
237.3
0.23 854E
07
36,74
0.43228E
04
0.17956E-02
0,6386-04
30,
0. 17875E-02
1.005
33
239.9
0. 241446
07
36.69
0143749E
04
0.18129E-02
0.648 E-04
30.
0.17832E-02
1.017
34
242.5
0. 244326
07
26,40
C*44270E
04
0.17910E-02
0.621 E-04
30.
0.17789E-02
1.007
35
245.1
0.247216
07
26.63
0.44788E
04
0.17961E-02
0.6616-04
30.
0.17748E-02
1.012
36
247.8
O.25O09E
07
36 • 27
0*453066
04
0. 17896E-02
0.7 146-04
30.
0.177 07 E-02
1.011
117
FUN 100 17A-1 *** DISCRETE HDLE RIG *** NAS-3- 14336
STANTON NUMBER DATA
TAce^
^ 21.51
DEG C
UINE =
ie.74 M/S
TINF= 21.38
DEG C
FHO =
1. 188
KG/M3
V IS
C= 0.15229F-04 M2/S
XVO= 21.0
CM
CP =
1012.
J/KGK
PR=
0.716
27C0HSL4G M=0.
,4
Th = 0 1
^/C-5
PLATE
X
RtX
TO
FEENTH
STANFDN NO
DST
DRE5N
M
F
T2
THETA
OfH
1
127.8
O.U73eE
07
36. 33
0.181775
04
0.23449E-02
0. 511 E- 04
28.
2
132.8
0. I2297E
07
36.36
O.i 9485E
04
0. 233865-02
0.5096-04
29.
0. 39
0.0126
23*45
0.138
0.020
3
137.9
0. I2 855t
07
36.34
Ci21760E
04
0.23301E-02
0.509E-04
31.
0.39
0.0128
23i72
0.156
0.020
4
143.0
0. 13414E
07
36. 34
0-24163E
04
0.22895E-C2
0. 507F-04
33.
0.39
0.0127
23-68
0.154
0 .020
c
148.1
0. 13972E
07
26. 36
0i25526E
04
0.22665E-02
0.5055-04
35.
0.39
0,0126
23162
0.149
0.020
6
153.2
0.14531E
07
36 c 40
C A2 8 82EE
04
0.221636-02
0.501E-04
36.
0.38
0.0123
23i69
0.153
0.020
7
158.2
0.15CB9S
07
36.26
0.31128E
04
0.22572E- 02
0.505 E-04
38.
0.39
0.0126
23-86
0.165
0.020
8
16 3.3
0, 15648E
07
36. 33
Ci33537E
04
0.22183E-C2
0o5 04E-04
39.
0.39
0.0125
23172
0.156
0.020
9
168.4
0.16206E
07
36,36
Ci35856E
04
0 .21767E-02
0.500E-04
41.
0. 39
0.0126
23175
0.158
0.020
10
173.5
0. 16764E
07
36.54
0J38193E
04
0. 219515- C2
0.502E-04
42.
0.38
0.0124
23i79
0.161
0.020
11
178.6
0. 17323E
07
36.34
C-40522E
04
0. 21703 E-02
C.500E-04
44.
0.39
0,0126
23.79
0.161
0.020
12
183.6
0. 1788 IE
07
36. 36
0*42 64 7E
04
0.2C8506-02
0.495E-04
45.
0.39
0.0125
23173
0,157
0.020
13
187.5
0 .18306E
07
35.79
0i44818E
04
0-203626-02
0.688E-04
46,
14
190.1
0. 18593E
07
55.79
0.4538BE
04
0.19243E-02
0.677E-04
46.
15
192.7
0. 16881E
07
36,15
0.45537E
04
0,16876E-02
0.673E-04
46.
16
195.4
0. 19170E
07
36, 21
0A46475E
04
0.184936-02
0.6 53 E-04
46.
17
198-0
0.19459E
07
36. 27
Oi470O3E
04
0.161766-02
0.644 E-04
46.
18
200.6
0. 197;^7E
07
36.27
0i47521E
04
0.17824E-02
0.633E-04
46,
19
203.2
0.20034E
07
36.27
Ci48CC5E
04
0. 15769E-02
0.609E-04
46.
20
205.8
0.20322E
07
34.68
0i4S563E
04
0.2300QE-02
0.723E-04
46.
21
208.5
0.20609E
07
36. 34
01491195
04
0.156006-02
0.601E-04
46 .
22
211.1
0.20897E
07
36.44
C149584E
04
0.16724E-02
0.603E-04
46.
22
213.7
0. 211856
07
36.40
fll50062E
04
0.16460E-02
0.586 E-04
46.
24
216.3
0.21474E
07
36.55
Ci50535G
04
0 .163866-02
Q.599E-04
46.
25
218.9
0.21763E
07
26. 4C
Ci510Q9E
04
D.16558E-02
0.592E-04
46.
26
221.6
0,220505
07
36.33
0i5l480E
04
0.161 79E-02
0.616E-04
46.
27
224.2
0.22338E
07
35.14
0.51947F
04
0.162075-02
0.5 37 E-04
46.
23
226.8
0.22625E
07
36. 31
Ca52415E
04
0 = 1631 lE-02
0. 622E-C4
46.
29
229.4
0.22913E
07
26. 21
0 *528315
04
0.1604CE-02
0.565E-Q4
46.
3C
232.0
0. 232015
07
36.74
Ci53346E
04
0. I6302E-02
0.601E-04
46 ■
31
234.6
0.234335
07
36 .69
0 *532155
04
0.16291E-02
0. 587E-04
46.
32
237.3
0. 25777E
07
36. 55
C<.54263£
04
0.I6166E-O2
G.5SIE-04
46.
33
239.9
0. 24066c
07
36.53
C154750E
04
0 ,162805-02
0.592E-04
46.
34
242.5
3.24354E
07
36. 21
G155219E
04
0,1 6290E-02
0,570 E-04
46.
35
245.1
0.24641E
07
26.44
Oi556S6E
04
0, U141E-02
0. 604E-04
46.
36
247.8
0. 249295
07
36. C6
0<!56 1505
04
0 ,iei24E-02
0.658E-04
46 .
UNCERTAINTY IN REX=279^2. UNCERTAINTY IN F = 0o05036 IN RATIO
RUN 100374
*** DISCRETE HOLE RIC NAS-3-14336
STANTON NUMBER DATA
TACB =
20.81
DEG C
UINF
X
l«.70 M/S
TINF= 20.69
DEG C
FHC =
1.194
KG/M3
Vise
* 0.15
125E-04 M2/S
XVQ- 21.0
CM
CP =
1012.
J/KGK
PR-
0i716
tin*
2700HSL40 M=0.
4 TF=1 P/D*£ ***
PLATE
X
REX
TO
PEENTH
STANTCN NO
OST
OREEN
M
F
T2
THETA
DTH
1
127.8
0.11 79 OE
07
26.33
Oil8258E
04
0.23403E-02
0.488 E-04
28.
2
132.8
0. 12351E
07
26. 26
Cil9478E
04
0.201 06 E-02
0.470E-04
33 .
0.37
0.0120
35i5S
0.951
0.020
3
137.9
0.12912E
07
36.38
Oi26887E
04
0.16555E-02
0.453E-04
42.
0,37
0-0120
36*47
1.006
0.02 0
4
143.0
0.13473E
0 7
26. 24
0i34518E
04
0.13919E-02
0.444E-04
49.
0.38
0.0122
36*87
1.034
0.020
5
148.1
0. 14034E
07
36-31
Oi42343F
04
0.12162E-02
0.443E-04
56.
0. 37
0.0120
36i53
1.014
0.020
6
153.2
0. 14595E
07
26. 23
Oi49864E
04
0 -12416E-02
0.440E-04
62.
0.39
0.0127
36i35
1.002
0*020
7
158.2
0.15156E
07
36. 33
0i57716E
04
0.12191E-02
0.439E-04
68.
0.38
0.0124
36.21
0.992
0.020
8
163.3
0.15717E
07
26.33
0*65 274E
04
0.11969E-02
0.438E-04
73.
0. 36
0.0118
36*76
1.028
0.020
9
168.4
0.16273E
07
26. 24
e i72728E
04
0.11419E-02
0.436E-04
77,
0.37
0.0120
36*24
0.993
0.020
10
173.5
0.16839E
07
36.31
Oi80028E
04
0 .112876-02
0.437E-04
82.
0. 38
0.0123
35*81
0.968
0.020
11
173 .6
0. 17400E
07
26.34
0i87338E
04
0, 1C889E- 02
0,4346-04
86 .
0.39
0.0125
35i5S
0.952
0.020
12
183.6
0.17960E
07
36.36
0i94645E
04
0.10709E-02
0.433E-04
89.
0.37
0,0120
35i3l
0.933
0.020
13
187.5
0.18387e
07
36. 23
0:lQ136E
05
0.1C778E-02
0.406E-04
91 .
14
190.1
0. 18676E
07
36 . 13
0410168E
05
0.110536-02
0.427E-04
91.
15
192.7
0. 18964E
07
26. 36
0*1 0200b
05
0.11136E-02
0.431 E-04
91.
16
195.4
0.19255E
07
36. 36
0J10232E
05
0. 11104E-02
0.424E-04
91 .
17
198.0
0. 19545E
07
26.26
0U0264E
05
0-11164E-02
0.427E-04
91,
IB
200.6
0.19834E
07
26.23
0il02S7E
05
0. llZlSE-02
0.4296-04
91,
IS
203.2
0.20123E
07
36.29
0il0329E
05
0.10931E-02
0.412E-04
91.
20
205.8
0.20412E
07
26- 26
0U0361E
05
0. 11041E-02
0.419E-04
91.
21
208.5
0.20701E
07
26.33
Oa0392E
05
0.10947E-02
0.4156-04
91.
22
211.1
0.20S89E
07
36.34
0il0424E
05
0.1C978E-02
0,4246-04
91 .
23
213.7
0.212J8E
07
36,23
0110456E
05
0.1C804F-02
0.415E-04
91.
24
216.3
0.21569E
07
26. 44
Qil0487E
05
0.10914E-02
0.4306-04
91.
25
218.9
0.21859E
07
36. 31
0il05L9E
05
0.110076-02
0.4256-04
91 .
26
221-6
0.22148E
07
36. 17
0il0551E
05
0.111Q4E-02
0.446E-04
91.
27
224-2
0.22437E
07
35,29
0il0582E
05
0. 1C59 5E-02
0.388E-04
91 .
28
226.8
0.22 72 5E
07
26. 23
Oil0613E
05
0.111316-02
0. 4526- 04
91.
2S
229.4
0.23014E
.0 7
26. IS
0ilO646E
05
0.11054E-C2
0.417E-04
91.
30
232.0
0. 23303E
07
26.44
0il0-678E
05
0.11589E-02
0.450E-04
91.
31
234.6
0.23592E
07
26.44
0il0711E
05
0-11346E-02
0.438E-04
91 .
32
237.3
0.23382E
07
36.27
<3U0744E
05
0.11523£-02
0.440 E-04
91 .
33
239.9
0, 24173E
07
26.23
CJ10778E
05
0,11711E-C2
0.448E-04
91.
34
242.5
0.24461E
07
26.02
0U0811E
05
0.11055E-02
0.416E-04
91-
35
245-1
0.24750E
07
36. 13
0U0844E
05
0,116996-02
0.463E-04
91 .
36
247.8
0.25039E
07
35.83
0a0878E
05
0.11610E-02
0.500E-04
91.
UNCERTAINTY IN BEX=2 8046.
UNCERTAINTY IN F=0*05036 IN RATIO
119
FUN
100174-1 ♦**
DISCRETE
HCLE RIG
NAS-3- 1433£
STANTON NIMBE^
DATA
***
2700HSL40 M-C.4
TH»0
P/0*5 **♦
RUN
100374 *♦*
DISCRETE
HCLE RIG
*•* NAS-3-14336
STANTON NUMBER
DATA
2700HSL40 H«0.4
TH-l
P/0«5
LINEAR SUPERPCSITICN IS 4PPLIEC TO STANTON NUMBER DATA FROM
RUN NUMBERS 10017-A-l AND 100374 TO OBTAIN STANTCN NUMBER DATA AT TH»0 AND TH-1
PLATE
RE XCOL
RE DEL 2
ST(TH«0)
REXHOT
RE CEL2
ST(TH*1»
ETA
STCR
F-COL
STHR
= -HOT
LDGB
1
1173846.0
1817.7
0.002345
1179040.0
1825.8
0.002340
UUUUU
1.040
0.0000
1.038
0.0000
1*038
2
1229690.0
1950.1
0.002395
1235131.0
1947.2
0.001991
0.169
1-057
0.0126
0.879
0.0120
2.713
3
1285534.0
2085.3
0.002450
1291222.0
2720.1
0.001638
01331
1.077
0.0128
0.720
0.0120
2.491
4
1341379.0
2222.1
0.002450
1347314.0
3479.4
0.001412
0i424
1.088
0.0127
0.627
0.0122
2.390
5
1397223.0
2358.4
0.002431
1403405.0
4240.2
0.001342
01448
1.086
0.0126
0.599
0.0120
2.329
6
1453067.0
2493.0
iQ.0Q2455l
1459496.0
4983.7
0.001251
01476
1.094
0.0123
0.573
0.0127
2.417
7
1508912.0
2628.2
1515568,0
5767.9
0.0012L5
01505
1.118
0.0126
0.554
0.0124
2.333
6
1*64756.0
2764.1
0.002411
1571679.0
6529.2
nr:’TOi2flgi
0.499
1.125
0.0125
0.564
0.0118
2.316
9
1620600.0
2897. 5
0.002367
1627770.0
7256.8
0.001155
01512
1.106
0.0126
0.540
0.0120
2.299
10
1676444.0
3030.7
0.002402
1683862.0
7990.9
0.001104
0*540
1. 132
0.0124
0.520
0.0123
2.323
11
1732289.0
3164.5
.Q.t,Q<?239a.
10,00229 li
1739953.0
£741.7
0.001035
01567
1.148
0.0126
0.497
0.0125
2.342
12
1768133.0
3295.1
1796044.0
9502.4
0.000996
01565
1.100
0.0125
0.478
0.0120
2*240
13
1830575.0
3391.2
0.002233
1838674.0
10216.3
C. 001 007
01549
1.142
0.515
14
1159334.0
3453.5
0.002090
1867561.0
1C246.0
0.001045
01500
1.061
0.531
15
1888094.0
3513.0
0.00204 5
1696448.0
102 76). 4
0.001057
01483
1-057
0.547
16
1916993.0
3571.2
0.001999
1925475.0
10306.9
0.001056
01472
L.051
0-555
17
1945893. 0
3628.2
0.001960
1954502.0
10337,6
0.001065
0*457
1.034
0.562
18
1974653.0
3684.0
0.001916
1.983389.0
103 6 8.5
0.001073
01440
1.004
0.562
19
2003412.0
3735.7
0.001675
2012276.0
10399,4
0.00105E
01359
0.889
0.561
20
2032172.0
3796.4
0.002542
2041163.0
1C429.3
0. 001016
0^600
1.354
0.541
21
2060932.0
3856.9
0.001654
2070051.0
1045J.4
0.001060
0.359
0.886
0.568
22
2089692.0
3906.4
0.001769
2096938.0
10490.0
C. 001056
01410
0.958
0.565
23
2118452.0
3957.5
0.001761
2427825.0
IC520.3
0.001039
01410
0.966
0.570
24
2147351.0
4008. 1
0.001750
2156852.0
10550.5
0.001051
0*399
0,930
0.559
25
2176250.0
4058.7
0.001768
2.185879.0
10581.0
0.001060
01401
0.961
B.576
26
2205010. 0
4108.9
0.0Q1721
2214766.0
10611.9
0.001073
01376
0-937
0. 584
27
2233770.0
4158.7
0.001735
22436 5 3.0
10642.1
0.001018
0i413
0.942
0.553
28
2262530. 0
4208.7
0.001736
2272540.0
10672.4
0.001075
0*381
0.944
0.584
29
2291290.0
4258.2
0. 001705
2301428.0
1C7 03.4
0.001069
0*373
0.912
0.572
30
2320050.0
4307.6
0.001726
2330315.0
10735.1
0.001124
0.349
0.926
0.605
31
2348810.0
4357.3
0.001729
23592 02.0
1076 7.2
0.001098
01365
0.950
0,603
32
2377709.0
4406.9
0.001711
2388229.0
1C799.3
0.001118
01346
0.948
0.620
33
2406606.0
4456.3
0.001721
2417256.0
1CB31.9
0.001138
0l339
0.950
0.628
34
243 5 368.0
4506.0
0.001735
2446143.0
1C863.8
0.001067
01385
0.967
0.595
35
2464128.0
4555.5
0.G01704
2475030.0
1C895.7
0,001137
0*333
0.960
0.641
36
2492867.0
4604.6
0.001704
2503917.0
10928.4
0.001128
01338
0.997
0.660
STANTON NUMBER RATIO BASED ON EXPERIMENTAL RAT PLATE VALUE AT SAME X LOCATION
STANTON NUMBER RATIO FOR TH«1 IS CGNVERTED TO COMPARABLE TRANSPIRATION VALUE
USING ALOGU * Bl/B EXPREISION IN THE BLOWN SECTION
120
RUN 073174 VELOCITY PROFILE
REX =
0.11423E 07
REM
C
2597.
XVO =
22.35 CK.
0EL2
0.240
UINF =
16,80 M/S
DEL99=
2.000
Vise =
0.15498F-04 M2/S DELI
=
0.334
PORT =
19
H
1.392
XLOC -
127.76 CM.
CF/2
= 0.17156E-02
Y( CM. )
Y/DEL
U(M/S) U/UINF
Y +
U +
0.025
0.013
7,25
G.431
11.4
10.42
0. 028
0.014
7.41
0.441
12.5
10.65
0.030
0.015
7.63
0,454
13,7
10.97
0.033
0.017
7,84
0.467
14.8
11.26
0.036
0.018
8, 16
0.486
16.0
11.72
0. 041
0.020
8.5C
C.506
18.2
12.22
0.048
0.024
8.9C
0.530
21.7
12.79
0.051
0.025
8.96
0.534
22.8
12.88
0. 058
0.029
9.31
0.555
26.2
13.39
0. 066
0.033
9.45
C.563
29.6
13.59
0. 076
0.038
9.7C
0.578
34,2
13.94
0.C39
0,044
9,96
0.593
39.9
14,31
0. U4
0.057
10.31
0.614
51,3
14.83
0.152
0.076
10,69
0.637
68.4
15.37
0.203
0.102
11.15
0.664
91.2
16.03
0.267
0.133
11.56
0.689
119.7
16.64
0,343
0.171
12.01
0,715
153.9
17,26
0.432
0.216
12.40
0,73 8
193,8
17.82
0.533
0.267
12.84
0.764
239.4
18.45
0.648
0,324
13.34
0.795
290.7
19.18
0.800
0.400
13.85
0,825
359.1
19.91
0.978
0.489
14.45
C.860
438.9
20.77
1.181
0.590
15.06
0.897
530,1
21.66
1.440
0.720
15.71
0,936
646 .4
22.59
1.664
0.032
16.19
0.964
746.3
23.28
1.9B1
0.990
16.61
0.989
889.3
23.88
2.362
1.181
16.80
1.000 1060.3
24.14
3.020
1.514
16.80
1.000 1359.0
24.14
fUN J73174 »** DISCHE7!; HOLE RIG *** NAS-3- 1433f STANION NUMBER DATA
TACe=
26.81
DEG C
U IMF
14.80 M/S
TINF= 26.68
OEG C
FHC =
1. 17 1
KG/M 3
V ISC
= 0.15622E-04 M2/S
XVG= 22.4
CM
CP =
1315.
J/KGK
PR=
0i717
2700S
TEPFP P/0 =5
PLATE
X
P.SX
TC
FE5NTH
STANTON KO
DS7
DREEN
SHTHEOI
1
127.8
0.11335E
07
39,35
Oi95676E
02
0.35028E-02
0.6836-04
2.
0.31739E-02
2
132.8
0- 118826
07
39.39
C.27670E
03
0.31248E-02
0.6526-04
3.
0.27968E-02
?
137.9
0.124286
07
39. 39
0i44390E
03
0.299646-02
0.6426-04
4.
0.26313E-02
4
143.0
0.12974E
07
39. 31
0*60297E
03
0.282706-02
0.6346-04
5.
0.25245E-02
5
148.1
0. 13521E
07
39.37
C.75534E
03
0-27515E-02
0. 6266-04
5.
0.24454E-02
6
153.2
0.14Q67E
07
39.43
C^90327E
03
0.26641E-02
0.6176-04
6.
0.23826E-02
1
158.2
0.14613E
07
'39. 39
0:10475E
04
0.26161E-02
0. 6166-04
6.
0-23305E-02
a
163.3
0.15159E
07
39. 41
Gill884E
04
0.2541 76-02
0.6106-04
7.
0.22858E-02
s
168.4
0.157.06E
07
39.41
Cil3265E
04
0.251376-02
0.6086-04
7.
0.22468E-02
10
173.5
0.16252E
07
29. 44
CU4621E
04
0.245356-02
0.603E-04
8.
0.22120E-02
11
178.6
0. 16798E
07
39.46
0U5952E
04
0.241716-02
0.6006-04
8.
0.218 08E-02
12
183-6
0.17345E
07
39. 54
Oa7268E
04
0.240 16E-02
0.5 95 6-04
8.
0.21524E-02
13
187.5
0.17760E
07
39.44
0^18241E
04
0.22480E-02
0.7956-04
9.
0.21324E-02
14
190-1
0. 130416
07
39.41
01188696
04
0.22150E-02
0.7916-04
9.
0.21196E-02
15
192.7
0. 18322 E
07
39.75
C.19409E
04
0.218 77E-02
0.7926-04
9.
0.21073E-02
16
195.4
0.18605E
07
-39.77
0120 102E
04
0.21648E-02
0.7746-04
9.
0.20953E-02
17
198.0
0. 18888E
07
29.81
01207056
04
0. 214316- C2
0.7706-04
9 .
0.20838E-02
18
200.6
0. 191696
07
39.75
C121313E
04
0. 21446 E-02
0.769E-04
9.
0.20728E-02
19
203.2
0.1945 IE
07
39. 69
0121913F
04
0.211806-02
0.7516-04
9.
0.20622E-02
20
205.8
0.197326
07
39.82
0.22509E
04
0.211506-02
0.7596-04
10.
0.20519E-02
21
208.5
0.2U013E
0 7
39.79
0123102E
04
0.2C9^1E-02
0.7486-04
10.
0-20419E-0?
22
211.1
0.202956
07
39.81
0.23691E
04
0.20913E-02
0.7566-04
10.
0. 203226-02
23
213.7
0. 205766
07
39. 73
C124274E
04
0.20465E-02
0.733E-04
10.
0.20229E-02
24
216.3
0- 20859E
07
39.84
0.24855E
04
0. 207626-02
0.7546-04
10.
0.20137E-02
25
218.9
0.211416
07
39. £4
Q125435E
04
0.20436E-02
0.7 396-04
10.
0.20048E-02
26
221.6
0.21423E
07
39.81
0126018E
04
Q.2C973E-02
0.766E-04
10-
0.19963E-02
27
224.2
0.217Q4E
07
39.43
0126628E
04
I0.22334E-02
1 0-7786-04
10.
0.19879E-02
28
226.8
0.219856
07
39. 86
C127222E
04
0- 198346-02
0.738 6-04
11.
0.19798E-02
29
229.4
0.22267E
07
39.67
0i27782E
04
0.199256-02
0.702 E-04
11.
0.19718E-02
30
232.0
0.22548E
07
43.09
0128347E
04
0.202 106-02
0.7466-04
11.
0-19641E-02
31
234.6
0.22 829E
07
40.05
0128916E
04
0-201686-02
0.730E-04
11.
0.19566E-02
32
237.3
0. 23112E
07
39.94
0129479E
04
0.198316-02
0.720 E-04
11.
0.19492E-02
33
239-9
0.23395E
07
39.86
0130042E
04
0.20099F-02
0.731E-04
11.
0-1942QE-02
34
242.5
0.23676E
07
39. 62
Q130601E
04
0.19633E-02
0-697E-04
11.
0-19349E-02
35
245.1
0.23957E
07
39.82
01311606
04
0-2C032E-02
0. 7486-04
IL.
0.1928LE-02
36
247.8
0. 24 239E
07
29.54
0131717E
04
0.1949 86-02
0.796E-04
11.
0.L9214E-02
RATI 3
1.104
1.117
1.139
1.120
1.125
1.118
1.123
1.II2
1.119
1.109
1.108
1.116
1.054
1.045
1.038
1.033
1.028
1.035
1.027
1.031
1.026
1.029
1.012
1.031
1.019
1.051
1.123
1.002
1.010
1.029
1.031
1.017
1.035
1.015
1.039
1.015
STANTON NLMBER DATA
RUN 090574 *** DISCRETE HOLE PIG NAS-3- 14336
TAOE =
27.69
CEG C
U INF
16.81 M/S
TINE= 27.56
DEG C
RHC-
1. 161
KG/N3
Vise
* 0.15796E-04 M2/S
XVG= 22.4
CM
CP =
1015.
J/KGK
PR=
01717
***
2700STEP10 M=0. 1
TH=0
P/0«5 ***
PLATE
X
REX
TO
REE NTH
STANTON NC
DST
DREEN
M
F
T2
THETA
OTH
1
127.8
0.1121 8E
07
38. 19
0196243E
02
0.35604E-02
0. 813E-04
2 .
2
132. 8
0. 11759E
07
38.19
Oi2758l£
03
0.30823E-02
0.772E-04
5.
0. 11
0-0035
28102
0.043
0.029
■a
137.9
0.12299E
07
33. 19
01449166
03
0.3C353E- 02
0.768E-04
7.
0. 10
0.0033
26169
0-106
0.029
4
143.0
0.12840E
07
38.23
Oi62760E
03
0.2E675E-02
0.7526-04
8.
0.10
0.0033
28*55
0.093
0.029
5
148.1
0.13381E
07
38.23
0179750E
03
0.2796CE-02
0.746E-04
9.
0.10
0.0033
28145
0.083
0.029
6
153.2
0.1392 IE
07
38.23
0.96012E
03
0.26709E-02
0.736E-04
11.
0. 10
0.0033
28.51
0.088
0.029
7
158.2
0, 14462E
07
38. 21
Cmi95E
04
0.264316-02
0.736 E-04
12 .
0-10
0.0032
28168
0.105
0.029
e
163.3
0. 15003E
07
38-19
0U2779E
04
0. 25381E-02
0.729E-04
12.
0.10
0.0032
28162
0.100
0.029
9
168.4
0- 1554 3E
07
38. 21
Qil4296E
04
0.24392E-02
0.721E-04
13.
0.10
0.0033
28158
0.095
0.029
10
173.5
0.16084E
07
38. 21
0115773E
04
0.23974E-02
0.718E-04
14.
0.11
0.0035
28156
0.094
0.029
u
178-6
0. 16 62 4E
0 7
38. 23
Oil7223E
04
0.23143E-02
0.711E-04
15.
0.10
0.0034
28166
0.105
0.029
12
183-6
0.17165E
07
38.27
C*18637E
04
U.22062E-02
0.702E-04
15.
0.10
0.0034
28161
0.098
0.029
13
187.5
0.17576E
07
37.73
0119724E
04
0.2244 IE- 02
0.812E-04
16.
14
190.1
0. 17854E
07
37.64
Oi20346E
04
0.221 75E-C2
0.835E-04
16.
15
192.7
0.18133E
07
37.94
0.20952E
04
0.21296E-02
0.814E-C4
16.
16
195.4
0.18413E
07
37.96
0i21540E
04
0.2C915E-02
0.790 E-04
16.
17
198.0
0. 18692S
07
37. sa
0.22120E
04
0 .2C668E-02
0.784E-04
16.
1£
200.6
0. 18971E
07
:7. 9 6
0122694E
04
0.20517E-02
0.7 79 E-04
16.
19
203.2
0. 19249E
0 7
37.94
0i23260E
04
0.2C097E-02
0.755E-04
16.
20
205.8
0. 19528E
07
38. Q4
01238226
04
0.20200E-02
0.765E-04
16.
21
203.5
O.19806E
07
37.98
Ci24383E
04
0.20106E-02
0.754E-04
17.
22
211.1
C.20C84E
07
38. 10
0i249 3 8E
04
0.1S678E-02
0.7 59 E-04
17.
23
213-7
0. 20363E
07
38. C4
0*25482E
04
0. 193786-02
0.739E-04
17.
24
216.3
0.20643E
07
38.11
0 42602 6E
04
0.19767E-02
0.7 62 E-04
17.
25
218.9
0. 20922E
07
38. 10
0126577E
04
0-1S623E-02
0.753E-04
17.
26
221 .6
0.21201E
07
3 8. C2
0427120E
04
0.19357E-02
0. 7816-04
17.
27
224.2
0.21479E
07
37. C5
C127662E
04
0. 19526E-C2
0.710E-04
17.
28
226.8
0.21758E
07
33.02
0128205E
04
0.19416E-02
0.788E-C4
17.
29
229.4
0. 22036E
0 ?
37. 96
0128743E
04
0.19168E-02
0.722E-04
17.
3C
232.0
0. 22315E
07
28.29
0*292816
04
0. 19465E-C2
0.760E-04
17.
31
234.6
0. 22593E
07
38. 29
0129822E
04
0.192826-02
0-741E-04
17.
32
237.3
0.22873E
0 7'
38. 19
C.30355E
04
0.1E998E-02
0.733E-04
17.
33
239.9
0. 23153E
07
38.13
C130886E
04
0.19113E-02
0.738E-04
17.
34
242.5
0.23431E
07
37. 92
C131416E
04
0.188496-02
0.712E-04
17.
35
245.1
0.23709E
0 7
33.08
0131944E
04
0.191CIE-02
0.759F-04
17.
3t
247.8
J.23988E
07
37.65
Ci32472E
04
0.1E734E-02
0.813E-04
18.
LNCrRTAINTY IN REX=2 7032
uncertainty in F = 0. 05037 IN RATIO
RUN 090674 DISCRETE HOLE PIG *** NAS-3-14326 STANTPN NUMBER DATA
TA06=
27.36
CEG C
U INF
■=
16.87 M/S
TINF* 27.24
DEG C
RHC*
1.162
KG/M3
Vise
= 0.15755E-04 M2/S
XVQ* 22.4
CM
CP*
1016.
J/KGK
PR=
01717
***
2 700STEP10 M=3.1
tl
X
p/D*5
PLATE
X
REX
TO
PEENTH
STANTON NO
OST
OREEN
M
F
T2
THETA
DTH
1
127.8
0.11285E
07
39-37
C.90674E
02
0.333466-02
0.698E-04
2.
2
132.8
0.1ia28E
07
29,37
Ci25571F
03
0.27347E-02
0.653E-04
5.
0.10
0.0031
36i6B
0.779
0.025
■3
137.9
0.12372E
07
29, 29
Ci52671E
03
0.24412E-02
0.632E-04
8.
0.08
0.0024
36*86
0.792
0.025
4
14 3.0
0.12 91 6E
07
39. 35
Oi76178E
03
O.23350E-O2
0.6 27F-04
9.
0.08
0.0027
36181
0.790
0.025
5
14fl.l
0.1346JE
07
2?. 35
0ilO024E
04
0.218696-02
0.618E-04
11.
0.07
0.0024
36*83
0.792
0.025
6
153.2
0. 14QC4E
07
29,35
C.12199E
04
0.20747E-02
0.612E-C4
12.
o.oe
0.0027
36164
0.777
0.025
7
158.2
3.14E48E
07
29. 25
C.14446E
04
0.2C051E-02
0.608E-04
13.
0.07
0.0022
36 165
0.777
0.025
8
163.3
0, 1509 IE
07
39. 35
Cil6460E
04
0 .192 5 66-02
0.604E-04
14.
0.07
0.0024
37101
0.806
0.025
9
168-4
0. 15635E
07
29. 37
C J1852QE
04
0.18394E-02
0.598E-04
15.
0.08
0.0025
36185
0.792
0.025
10
173.5
0.16179E
07
39. 41
0*20568E
04
0.17525£-02
0. 592E-04
16.
0.09
0.0029
36165
0.773
0.025
11
178.6
0. 16723E
07
29.41
0122713F
04
0.167766-02
0.5B8E-04
16.
0.08
0.0026
36i72
0. 780
0.025
12
183.6
Q.17267E
07
29.41
0i24723E
04
0- 162566-02
0.586E-04
17.
0.08
0.0026
36187
0.792
0.025
12
187. 5
0.17680E
07
39.29
0.26543E
04
O.17220E-O2
0.642F-04
18.
14
190.1
0. 17960E
07
39. 1C
C.27C42E
04
0,18322E-C2
C.680E-04
18.
15
192.7
0.18 240 E
07
39.41
0*27550F
04
0.17910E-02
0. 6786-04
18.
16
195-4
0.1d522E
07
39.41
0i28 0 51E
04
0.17839E-02
0.666E-04
18.
17
198.0
0. 13b03£
07
39.39
0.28554E
04
0.1E04.1E-02
0.672E-04
18.
18
200-6
0. 1908 3E
07
29. 39
C129Q57E
04
0.17888E-02
0.6696-04
18.
19
203-2
0.19363E
07
39. 37
0.29555E
04
0.175e9E-02
0.651E-04
18.
2C
205.8
0. 19643E
07
39.43
0130054F
04
O.179 04E-O2
0.666E-04
18.
21
208.5
0.19923E
07
29.4 2
0.30551E
04
0. 17517E-02
0.654E- 04
18.
22
211.1
0.20203E
07
39.37
0i31049F
04
0.17949E-02
0.6726-04
18.
23
213.7
0.20483E
07
25. 21
C131548E
04
0.176E4E-C2
0.657E-04
18.
24
216.3
0.20765E
07
39.48
C132043E
04
0.17623E-02
0.6 74E-04
18.
25
218.9
0.2ia46E
07
59.37
0*32544E
04
0.180586-02
0.677 E-04
18.
26
221.6
0.21326E
07
29.24
C*33050E
04
0.1E058E-02
0.705E-04
18.
27
224.2
0.21606E
07
28, 36
Oi33549E
04
0.17519E-02
0.6 22 E-04
18.
28
226-8
0.21887E
07
39.29
0*34044E
04
0.178C1E-02
0.706E-04
18.
29
229.4
0.2216*7E
07
39.20
0.34540E
04
0.17578E-02
0.649E-04
19.
30
232-0
0.22447E
07
39.46
0i35043E
04
0.1B33flE-02
0.6 95 E-04
19.
21
234.6
0.22727E
07
39.50
0135548E
04
0.176UE-02
0.672E-04
19.
32
237.3
0. 230.0 8E
07
39.2?
C436G50E
04
0.1E104E-02
0.675E-04
19.
33
239.9
0.23290E
07
39.27
C.36556E
04
0.18020E-02
0.682E-04
19.
34
242.5
0-23570E
07
39.05
0i37058E
04
0.17756E-02
0.654E-04
19.
35
245.1
0.238506
07
39.22
0137560E
04
0-ie08.4E-02
C.700E-04
19.
36
247.8
0.24130E
07
59.01
Qi38064E
04
0.178 lOE-02
0.747E-04
19.
UNCERTAINTY IN REX=27192
UNCERTAINTY IN F*X),05036 IN RATIO
RUN 09057^ =4<’5‘* DISCRETE HCLE SIS NAS-3-1'^336 STANTON NUMBER DATA
2700STEP10 f*=0,l TH^O P/D=5 ***
RUN
090674
C ISC RET E HCLE RIG
NAS- 3- 143 2
6
STANTON NLi'IDEP
DATA
2700STEP10
C,1 TH
=1 P/D=5
***
L. I >i i
AP, SUFr:RPOSIT.l
C N 1 S A
,TPUi:0 TU S
T ANTON NUMBER
DATA FRCM
RUN
rNUMOERS 090574
AND
C90674 TO
OBTAIN STANTCN NIJR’BER DATA AT
TH=0 AND
TH = 1
ATE
rexcql re
DEL2
ST :th==o 3
REXHOT RE
CEL 2
in
-i
X
II
ETA
STCR
F-COL
STHR
s-HOT
,3GB
1
1121310.0
96 , 2
0.00 3 560
1128452, 0
90,7
0.003335
UUUUU
1.016
0,0000
0,952
0.0000
0.952
2
117 5873,0
2 76 .4
0. C03103
1182835,0
252.9
C. 002630
0. 152
0.814
0.0035
8.940
0.3031
1,419
3
1229936,0
444.0
0.CO3098
1237218.0
553.2
0,002262
0.270
0,909
0.0033
0.859
0.0024
1,267
4
1283999,0
607.3
0.00 2944
1291602,0
006.7
0.002174
0.262
0.931
0,0033
B.861
0.0027
1.330
5
1338063.0
764,5
0. 002872
1345985.0
1069.2
0.002006
0.302
0.960
0,0033
9.620
0. 0024
1.240
6
1392126. 0
916.3
0.002744
1400368.0
1303.4
0.001891
0.311
0,958
0,0033
0.793
0.0027
1.276
7
1AA6189. 0
1064.4
0. C02734
1454751,0
1550.2
0.001796
0 1343
0.990
0.0032
0,770
0.0022
1-185
3
1500252.0
1209.3
0. C02628
1509134,0
176 8. 1
0.001746
0*336
0.983
0.0032
0.763
0.3024
1.207
9
1554315. 0
1348,6
0,002522
1563518.0
19 89,2
0.001668
01339
0,969
0.0033
0.742
0.0025
1.212
10
1608378.0
1483.9
0.C02486
1617901.0
2211.9
0.001549
0*377
0.979
0.0035
6.700
0.0029
1.239
11
1662442. 0
1616.2
0.C02407
1672284.0
2450.7
0.001467
0*390
0.969
0.0034
0.673
0.0026
1,173
12
1716505.0
1743.3
0. C02292
1726667.0
2672.5
C. 001444
0*370
0,941
0,0034
0.671
0.0026
1.179
13
1757593.0
1837 .6
0. C02321
1767999.0
2877. 2
0.001559
0.329
0.966
i.730
14
1785435.0
1901 .6
0. C02274
1796006.0
2923.0
0.001712
0*247
0.955
0.807
15
1813278.0
1963 .7
0.C02180
1824013.0
2970.6
C. 001685
0*227
0.923
0.799
16
1841255, 0
2 023.9
0.002137
1 652157.0
3017.9
0,001688
0.210
0.913
0.805
17
1869233.0
2083 .0
0.002106
1880300.0
3065.7
0.001722
0*182
0.907
0.826
18
1897075, 0
2141 .5
0.00209 1
19C8307.0
311 3.8
0.001706
0*184
0.907
0.823
19
1924918.0
2199,2
0.002047
193631 5.0
316 1.3
0.001660
0*179
0.895
C.814
20
195276C. 0
2256,3
0.002053
1964322.0
3209.1
0.001729
0.158
0.904
0.842
21
1980603.0
2313.5
0. CG2C49
1992330.0
32 56.8
C. 001671
0*185
0.908
0.818
22
2003446, 0
2 369,3
0. 001993
2020337.0
3304.6
0.001741
0*127
0. 889
6.656
23
203628E.0
2424.5
0, C01563
2048344.0
3353.0
0,001715
0*126
0.882
0.648
24
2064266, 0
2430 .3
0.C020C8
2076487.0
3400.9
C, 001695
01156
0, 908
Q.841
25
2C92243,0
2536 .0
0. C01565
2104631,0
3449.3
C, 001757
0,115
0.903
0.876
26
2120C86.0
2590,9
0.00 1955
2 132638.0
3498.6
0,001765
0.097
0, 894
0.884
27
2 147 523. 0
2645,3
0.001582
2 160645. U
354 7.1
0,001689
0 * 148
0.912
0.849
28
217577 1. 0
27U0 -B
0.C01565
2 188653,0
359 5.0
C.00173C
0*120
0.909
0.873
29
2 20 3614.0
2735 ,2
0.001940
2216661,0
3643.2
0.001700
0.120
0.903
0.866
30
2231456. 0
2b09 . 7
0. C01966
2244668.0
3692.3
0.001797
0.086
0.919
0.914
31
2259299. 0
2364, 3
0.C01552
2272675.0
3741.6
0.001717
0*121
0,918
0.877
32
2287276.0
2918.1
0. CC 1913
23CC816. 0
3790.7
0.001782
0 .063
0.904
0.914
33
2315254. 0
2971,7
O.C01927
2328962,0
3840.4
C. 001768
0.083
0.915
13.910
34
2343 C56. 0
3025.0
0, C019C1
2356969.0
2889.6
C. 001741
0*004
0,907
fi.899
35
2370939. 0
3078 . 3
0. GO 1925
2384976.0
3938.9
0,001777
0.077
0. 923
0.921
36
2398 781.0
3131 .5
0, C01fc87
2412984.0
3988.4
0.001752
0 .372
0.909
0.911
STANTCN NUMBER RATIO BASEC ON 5T* PR^*0 . 4= 0 .029 5 * P EX** (- .2 ) =» ( 1 « X I / < X-XVO » > **0 .9 ) ** t - 1 . /9 . >
STANTON NUMBER PATIO FOR TH=i IS CCNVERteO TQ CCNFARABLE TRANSPIRATION VALUE
LSTNG ALCGIl + B ) / tl EXPRESSICN IN THE BLOWN SECTION
125
RUN
C80274
*** DISCRETE HOLE
RIG *** NAS-3-
14336
STANTCN NUMBER DATA
TAOB=
28.65
DEG C
UINF
' =
U.80 M/S
TINF= 28.53
DEG C
PHO =
1.164
KG/M3
Vise
;= 0.15
775E-04 M2/S
XVO* 22.4
CM
CP=
1016.
J/ KGK
PR=
0i717
***
2700STEP20 M=0. 2
TH=0
P/D*5
PLATE
X
PEX
TO
REENTH
STANTON NO
DST
ORFFN
M
F
T2
THETA
OTH
X
127.8
0.1122 5E
07
40. 03
0i89744E
02
0.331796-02
0.733E-04
2.
2
132.8
0.11766E
07
39.96
0i26141E
03
0.30285E-C2
0.714E-04
6.
0.20
0.0066
29.12
0.052
0.027
3
137.9
0.12307E
07
39.98
Oi44003E
03
3.28841E-02
0.702E-04
9.
0.20
0.0065
29*50
0.085
0.027
A
143,0
0.12848E
07
39.98
0.62375E
03
0.27989E-C2
0.696E-04
12.
0.20
0.0064
29*51
O.OB6
0.027
5
148.1
0.13389E
07
39.94
0.80229E
03
0.26996E-02
0.690E-C4
14,
0.20
0.0064
29*41
0.077
0.027
6
153.2
0.13930E
07
39. 96
Ci97262E
03
0.26049E-02
0.683E-04
16.
0.20
0,0064
29150
0.085
0.027
7
158.2
0.14471E
07
39.96
0-11415E
04
0.25536F-02
0.679E-04
17.
0.20
0.0064
29159
0.093
0-027
8
163.3
0. 15012E
07
39. 96
0.13C97E
04
0.24723E-C2
G.674E-04
19.
0.20
0.0065
29157
0.091
0.027
9
168.4
0.15553E
07
39.96
0il4740F
04
0.2410BE-02
0.669E-04
20.
0.20
0.0065
29152
0.087
0.027
1C
173.5
0. 16094E
07
39.98
0.16341E
04
0.23882E-02
0.6676-04
21-
0.20
0.0063
29146
0.082
0.027
11
178.6
0.16635E
07
39.96
0417905E
04
0.23551E-02
0. 666E-04
22.
0.20
0.0065
29150
0.085
0.027
12
183.6
0.17176E
07
40.00
Oil9447E
04
0.22403E-02
0.656E-04
23.
0.20
0.0064
294 51
0.086
0.027
13
187.5
0.17587E
07
39. 5C
Ci20659E
04
0.220C6E-C2
0.792E-04
24-
14
190.1
0.17866E
07
39.33
0*21278E
04
0.22410E-02
0.824E-C4
24.
15
192.7
0.18144E
07
39.67
0A21892E
04
0.21609E-02
0.811E-04
24.
16
195.4
0.1842 4E
07
39.73
.0i22487E
04
0.21029E-02
0.781E-04
24.
13
198.0
0.18704E
07
39. 7 9
Ci23066t
04
0.20635E-02
0.771E-04
24.
18
200.6
0.189B3E
07
89.75
0i23642E
04
O.2C510E-O2
0.765E-04
24.
19
203.2
0.19 26 IE
07
29.73
0424207E
04
0.20044E-02
0.741E-04
24.
20
205.8
0.19540E
07
29.84
0.24764E
04
0. 198 75E- 02
0.742E-04
24.
21
208.5
0.1981 9E
07
39.81
Q.25316E
04
0.19716E-02
0.731F-04
24.
22
211.1
0.20097E
07
39. 88
Ci25S61E
04
0.19319E-02
0.733E-04
25.
23
213.7
0.20376E
07
39.81
0i26396E
04
0. 191026-02
0.716E-04
25.
24
216.3
0.20656E
07
39. 90
0*26933E
04
0.19336E-02
0.735E-04
25.
25
218.9
0.209-366
07
39.90
0427468E
04
0.19024E-02
0.721E-04
25.
26
221.6
0.21214E
07
39, 84
Ci280G5E
04
0.19539E-02
0.746E-04
25.
27
224.2
0.21 493 E
07
39. 52
Oi28568E
04
0.2C767E-02
0.756E-04
25.
28
226.8
0.21772E
07
39. 94
Q629116E
04
0.1£586E-02
0.726E-04
25.
29
229.4
0.22Q50E
07
39.73
0i29638E
04
0. 18828E-02
0.692E-04
25.
30
232.0
0-22329E
07
40-09
0.30162E
04
0.187466-02
0.725E-04
25.
31
234.6
0.22697E
07
40. C7
0;30684E
04
0.18692E-02
0.710E-04
25.
32
237.3
0.22887E
07
39.96
0i31203E
04
0.16524E-02
0.705E-04
25.
33
239.9
0.23167E
07
39-88
Ci31724E
04
0.1E818E-02
0.717E-04
25.
3 ^
242.5
0.23446E
07
39.64
0.32245E
04
0 .18540E-02
0.688 F-04
25.
35
245.1
0.23725E
07
39. £2
C132764E
04
0.1E683E-02
0.734E-04
25.
36
247.8
0.24003E
07
39.58
0.33278E
04
0.18182E-02
0.783E-04
25.
UNCERTAINTY IN REX=2704«. UNCERTAINTY IN F=0. 05037 IN RATIO
FUN 080374 ♦>*. DISCRETE HOLE RIG NAS-3- 1433«
STANTON NIWBER DATA
TACB=
26.81
DEG C
UINF
X
1*.71 M/S
TINF* 26.60
DEG C
RHC=
1 .173
KG/M3
V ISC
* 0.15612E-04 M2/S
XVO= 22.4
CM
CP =
1013.
J /KGK
PR =
0.715
***
2700STEP20 M=C
1.2
TH = 1
P/D»5
PLATE
X
REX
TO
REENTH
STANTON NO
DST
DREEN
M
F
T 2
THETA
DTH
1
127.0
0.1128CE
07
41.32
0J88229E
02
0.324616-02
0.564 E-04
2.
2
132.8
0. 11823E
07
41.36
0-24652E
03
0.257786-02
0.538E-04
9.
0. 19
0.0062
41100
0*975
0.021
1
137.9
0.12367E
07
41.38
0 469896E
03
0.204076-02
0.508E-04
16.
0.16
0.0060
4 U 42
1.002
0.021
4
143-0
0.12911E
07
41.22
OaIISQIE
04
0.1f855E-C2
0.502E-04
20.
0.18
0.0058
4 U 83
1.035
0.021
c
148.1
0. 13454E
07
41.32
0415552E
04
0. 17385E-02
0.495E-04
24.
0- 18
0.0058
4 U 34
l.OOI
0.021
6
153.2
0.13998E
07
41. 21
0il9633E
04
0.16639E-02
0.493E-04
27.
0.18
0.0057
4 U 46
1.011
0.021
7
15 8.2
0.14541c
07
41-34
0.23666E
04
0.156286-02
0.487E-04
30.
O.IB
0.0059
41*29
0.996
0.021
8
163.3
0. 15G85C
07
^1.21
Oi27690E
04
0.15242E-02
0.487E-04
32.
0. 19
0.0060
42143
1.077
0.022
9
168.4
0.15629E
07
41.36
0432002E
04
0.14368E-02
0.4826-04
35.
0.18
0.0060
41129
0.995
0.021
13
173.5
0. 16172E
07
41. 21
0435997E
04
0-14075E-02
0.482 E-04
37.
0.18
0.0059
40139
0.938
0.021
11
173.6
0. 167I6E
07
41.24
0*39756E
04
0. 13603E-02
0.479E-04
39-
0.18
0.0060
40*04
0.911
0.021
12
183.6
0.17259E
07
^1- 36
0.43442E
04
0.1345^E-02
0.478E-04
41.
0.19
0.0061
40141
0.935
0.021
13
187.5
0.17672E
07
40.28
C447C82E
04
0. 120556-02
0,4416-04
42.
14
190.1
0. 17952E
07
39.88
04474436
04
0. 13684E-02
0.5226-04
42.
15
192.7
0.16232E
07
40. C5
U47E31E
04
0.14015E-02
0. 5426-04
42.
16
195.4
0. 18514E
07
40.03
0448227E
04
0 .142 14E-02
0.5426-04
42.
1?
198.0
0. 18795E
07
40.01
0448629E
04
0. 14528E-02
0.553E-04
42.
18
200.6
0.190J5E
07
39.96
0.49037E
04
0.14539E-02
0.554E- 04
42.
19
20 3.2
0. 19355E
97
39, 90
0449443E
04
0 .14453E-02
0.542 E-04
42.
20
205.8
0. 19635E
0 7
29.96
0i49853E
04
0. 14778E-02
0.555E-04
42.
21
208.5
0.19915E
07
39.98
0.50262E
04
0.14401E-02
0.548 E-04
42.
22
211.1
0-2019 5£
07
39.90
0*50672E
04
0.1485CE-02
0. 5636-04
42.
23
213.7
0. 20475E
07
39.90
0451084E
04
O.14505E-O2
0.552E-04
42.
24
216-3
0.20756E
07
40. G7
CA51492E
04
0.14539E-02
0.567E-04
42.
25
218-9
0.21037E
07
29. 94
0*51905E
04
0.14897E-02
0.564F-04
42.
26
221.6
0.21317E
07
39.90
0;52329E
04
0.15345E-02
0. 5846-04
42.
27
224.2
0.21597E
07
39.77
C*52772E
04
0.162706-02
0.601E-04
42.
28
226.6
3. 21877E
07
40.C1
0453207E
04
0.14766E-02
0-5 74 E-04
42-
29
229.4
0.22 15 7E
07
B9.84
Oi53618E
04
0. 14530E-O2
0.544E-04
42 .
30
232.0
0.2243 7E
07
40.01
0454038E
04
0.15463E-02
0.591E-04
42.
31
234.6
0.22717E
07
40. C3
01544656
04
0.15022E-02
0.577E-04
42.
32
237.3
0. 2299 8 E
07
39.81
0454892E
04
0.1E420E-02
0.580E-04
42.
33
239.9
0.232B0E
07
39.82
C155322E
04
0.15275E-02
0.585E-04
42.
34
242-5
0.23560E
07
39.60
0*557476
04
0.15036E-02
0.559E-04
42.
35
245.1
0.23840E
07
29-73
C156175E
04
0.15525E- 02
0.608E-04
42.
36
247.8
0.24120E
07
39.48
01566056
04
0.15165E-02
O.640E-O4
42.
UNCERTAINTY IN REX=2718C. UNCERTAINTY IN F»C. 05037 IN RATIO
127
RUN 080274
OlSCPe/e HOLE RIE NAS-3- 14336
STANTCN NUMBER DATA
•"** 27CCSTEP20 t<»C.2 TH*C P/C«5 »**
RUN (80374 *** CISCRETE HCLF RIG **» NAS*3- 14336 STANTON NIW0ER CATA
*»* 2700STRP20 M»0.2 TH»1 P/0=5 »**
LINEAR SUPERPOSITION I:i APPLIED TO STANTCN NUMBER CATA FROM
RUN numbers 080274 AND 080 374 TO CBTATN STANTON NUMEER DATA AT TH»0 AND TH«1
PLATE
REXCOL
RE DtL2
ST( 7H = {)J
REXhOI
RE prL2
ST(TH*U
ETA
STCR
F-COL
STHR
F-HOT
LOGS
1
1122526.0
39.7
0.0033 18
1127970.0
86.2
0.003246
UUUU'J
0.947
0.0000
0.927
0.0000
0.927
2
1176624.0
262.1
O.C03054
1182330.0
246.2
C. 002566
0.160
0.800
0.0066
fl.916
0.0062
1.T97
3
1230722.0
424.4
0.002947
1236690.0
706.3
0.002030
04311
0.664
0.0065
1.770
0.0060
1.650
4
1284819.0
582.1
D. C02ee3
1291050.0
1136.9
3.001904
0.340
0.911
0.0064
0.753
0.0058
1.642
5
1338917.0
735.4
0.C02783
1345410.0
1552.1
0.001757
0*369
0.929
0.0064
0.717
0.0058
1.623
6
1393015. 0
883.4
3.002668
1399770.0
1960.5
0.001670
0.379
0.938
0.0064
0.700
0. 0057
1.615
7
1447112.0
1027.7
0.C02650
1454130.0
2360.7
0»OQIg67
0. 409
0.959
0.0064
0.671
0.3059
1.616
8
1501210.0
1168.8
J. 002565
1508490.0
2765.3
fO. 001561 I
0.391
0.958
0.0065
0.682
0. 0060
1.660
9
1555308.0
1305.8
0.C02502
1562850.0
3173.5
G, 001474
0.411
0.960
0.0065
0.655
0.0060
1.636
10
160 9 4 05. 0
1440.6
0.002482
1617210.0
3574.6
0.001370
0.448
0.976
0.0063
0.618
0.0059
1.595
11
1663503.0
1574.1
0. C02454
1671570.0
3967.1
C. 001271
0*482
0.986
0.0065
0.582
0.0060
i.569
12
1717601.0
1703 .6
lO. 0023321
1725930.0
4359.8
1 0.001263 i
01458
0.956
0. 0064
0.586
0.0061
1.606
13
1758715.3
1798.8
3.002302
1767244.0
4741.9
0.001114
04516
0.957
0.522
14
1786575.0
1863.4
0.002330
1795239.0
4715.6
0.001288
01447
0.977
8.607
15
1814435.0
1927.1
0.002238
1823235.0
4812.3
0.001332
0*405
0.947
0.631
16
1842431.0
1988.6
0.C02172
1851366.0
4850.0
0.001359
0*375
0.927
0.647
17
1870426.0
2048.5
0.002126
1879497.0
4888.6
0.001397
0.343
0.914
0.669
18
1898287.0
2107.6
O.C02112
19C7493.0
492 7.8
0.001399
04338
0.915
0.674
19
1926147.0
2165.8
0.002061
1935488.0
4967.0
0.001394
0*324
0.900
0.675
23
1954007.0
2223.0
0.C02039
1S63483.0
50C6.5
C. 001431
0.29B
0.897
0.696
21
1981863.0
2279.7
0.002026
1991479.0
5046.1
0.001391
0.313
0.897
0.680
22
2009728.0
2335.6
0.C01977
2019474. U
5085.8
0.001444
0.270
0.881
0.709
23
203758 8.0
2390.4
0.001956
2047470.0
5125.9
0.001417
04276
0.878
8.699
24
2C65S84.0
2445.4
0.001983
2075601.0
5165.5
0.301410
0.289
0-895
0.699
^3
2093579.0
2SOO.I
0. C01944
2103732.0
52 0 5 .6
0.001452
0*253
0.863
0.723
26
2121440.0
2555.1
0.001997
2131728.0
5247.0
0.301496
0*251
0.912
0.748
27
214930C.0
2612.5
0.002123
215S723.0
5290.2
C. 001587
0*253
0.976
0.797
25
2177160.0
2668.6
0.001B98
2187718.0
5332.6
C. 001441
0*240
0.877
0.727
29
2205C21.0
2721.9
0.001927
2215714.0
5372.6
0.001414
0*266
0.895
0.716
33
22J2881.0
2775.4
0.C019C8
2243710.0
5413.7
0.001516
0*205
0.892
0.771
21
226 J741.0
2828.6
0.001907
2271705.0
5455.5
0.001466
0*230
0.896
0.749
32
2282736.0
2881.5
0.001884
2299836.0
5497.3
0.001513
0.197
0.890
0.775
23
2 316 73 2. 3
2934.5
0.001918
2327967.0
5535.5
0.001495
0*221
0.910
0.768
34
2344592.0
2987.6
0.001890
2355963.0
5581.0
0.001471
0.221
0.901
0.759
35
2372453. 0
3040.5
0. 001900
2383958.0
5623.0
3.001523
0.198
0.910
0.789
36
240J313.0
3092.8
0.C01849
2411953.0
5665.2
0.001489
0*195
0.890
8.774
STANTCN NUMBER RATIO BASEC ON ST APR**0.4=0 .029 E*RE >♦*( -. 2) •« 1.- ( XI /( X-XVOI l**0.9| **(-l . /9. .
STANTCN NUMBER RATIO FOR TH»1 IS CCNVERTEO TO COMPARABLE TRANSPIRATION VALUE
LSING ALOGd ♦ BJ/B EXPRESSICN IN THE BLOWN SECTION
RUN 090374 DISCRETE HOLE RU NAS-3-14336 STANTON NUMBER DATA
TACB*
26.08
DEG C
UiNf
16.87 M/S
TINF* 25.95
DEG C
RH0»
1. 167
KG/M3
V I SC
« 0.15649E-04 M2/S
XVC* 22.4
CM
CP»
1015.
J/KGK
PR»
0a717
***
2700STEP30 MaO.3
o
H
P/0^5
PLATE
X
RE X
TO
PEENTH
STAKTCN NO
DS T
OREEN
M
F
T2
THETA
DU
1
127.8
0-11361E
07
37.51
01997C9E
02
0.36423E-02
0.755E-04
2.
2
132.8
0.11 908E
07
37.56
X)i28704E
03
0.32007E-02
0.714E-04
8.
0.29
0.0093
26131
0.031
0,027
3
137.9
0. 12456E
07
37-54
C447214E
03
0-25776E-C2
0.698E-04
13 .
0.29
0.0094
26*65
0.060
0.026
A
143.0
0. 13C03E
07
37-54
O466340E
03
0. 28666 E-02
0.690E-04
16.
0.29
0.0095
26164
0.059
0.026
5
146.1
D.13551E
07
37. 54
0i846eeE
03
0.27846E-02
0.684E-04
19.
0.29
0.0095
26164
0.060
0.026
6
153.2
0. 14098E
07
37.56
0il0308E
04
0 .27331E-02
0.679E-04
22.
0. 29
0.0093
26165
0.060
0.026
1
150.2
0.14646E
07
37. 56
0il2CS7E
04
0.26837E-C2
0.675E-04
24.
0-29
0.0093
26*74
0.068
0.026
8
163.3
0.15194E
07
37.58
0*13889E
04
0.26049E-02
0.669E-04
26.
0.29
0. 0094
26179
0.072
0.026
9
168.4
0. 15741E
07
37-58
0il5673E
04
0.25524E-02
0.665E-04
28.
0.29
0.0095
26174
0.067
0.026
10
173.5
0. 16289E
0 7
37.58
CU7425E
04
0.25670E-02
0.666E-04
29.
0.29
0.0093
2616B
0.062
0.026
11
178.6
0. 16836E
07
37- 58
flU9132E
04
0.25053E-?)2
0.662E-04
31.
0-29
0.0093
26174
0.06 8
0.026
12
183.6
0.17384E
07
37.58
0i2O8l5E
04
0.23768E-02
0.653E-04
33.
0.29
0.0093
26171
0.065
0.026
13
187.5
0.17B00E
07
36.99
0422130E
04
0.23355E-02
0.821E-04
33.
14
190.1
0.18Q82E
07
36. 90
Qi22782E
04
0.228066-02
O.033E-O4
33.
15
192.7
0.18364E
07
37.22
Oi23417E
04
0.221E6E-02
0.822E-04
33.
16
195.4
0. 18647E
07
37- 26
Ci24C34E
04
0.21553E-02
0.7906-04
34.
17
198.0
0.18930E
07
37.31
012463 EE
04
0.21224E-02
0.782E-04
34.
16
200.6
0.19212E
07
37.21
0i25231E
04
0.2C817E-02
0.768 E-04
34.
19
203.2
0. 19494E
07
27.33
0i25809E
04
0. 20087E-02
0.737E-04
34.
20
205.8
0.19776E
07
37.43
Q126375E
04
0.20042E-02
0.740E-04
34.
21
208.5
0.20058E
07
27.37
0126940E
04
0.19963E-02
0.731E-04
34.
22
211.1
0.20 34 OE
07
37.47
C127496E
04
0.19435E-02
0.730 E-04
34.
23
213.7
0.20622F
07
37.39
012B042E
04
0. 19251E-02
0.713E-04
34.
24
216.3
0.20905E
07
37.51
0 428586E
04
0.19304E-02
0.7 29 E-04
34.
25
218.9
0.21189E
.0 7
37.45
0a29l30E
04
0.192 2 2 6 -02
0.72 lE-04
34-
26
221.6
0. 21471E
07
37.33
0*29671E
04
0. 190 72E-02
0.752E-04
34.
27
224.2
0.21753E
07
36.27
Ci30215E
04
0.19522E-02
0.683E-04
34.
26
226.8
0.22035E
07
37.37
0130759E
04
0.190036- 02
0.758E-04
34.
29
229.4
0.2231 7E
07
37. 28
0131296E
04
0.19066E-02
0.697E-04
34.
30
232.0
0.22 5©9E
07
27-66
0i31835E
04
0.190 83E-02
0.730E-04
34.
31
234.6
0.228eiE
07
S7. 62
0i32373E
04
0.19024E-02
0.713E-04
34.
32
237.3
0.23164E
07
37.51
0i32 9CBE
04
0. ie887E-02
0.709E-04
34.
32
239.9
0.23447E
07
37.47
0133441E
04
0.1E885E-02
0.7 13 E-04
34.
34
242.5
0.23729E
07
37. 22
0*33974E
04
0.1 E856E-C2
0.691 E-04
34.
35
245.1
0.2401 IE
07
37.41
0134 5 09E
04
0. 19042E-02
0.737E-04
34.
36
247.8
0.24293E
07
27. 16
0*3504 IE
04
0.18632E-02
0.792E-04
34-
UNCERTAINTY IN REX=27376
U^CERTAINT¥ IN F=0-05026 IN RATIO
RUN 090474 DISCRETE HOLE RIC *** NAS-3- 14336 STANTON NUMBER DATA
TACB=
: 26.90
DEG C
UINF=
16.84 M/S
TINF= 26.78
DEG C
FHO=
1.160
KG/M3
VISC= 0.15753E-04 P2/S
XVO= 22.4
CP
CP =
1017.
J/KGK
PR =
04718
***
2 700STEP 3D M=i
3. 3
TH = 1
P/0=5 ***
PLATE
X
REX
TO
REENTh
STAATCN NO
CST
OREEN
M
F
T2
THETA
1
127,8
0.11270E
07
43.11
0194222E
02
0.34694E-02
0.545E-04
2.
2
132.8
0.11814E
07
43.09
0.26 167E
03
0.26963E-02
0-496 E-04
12.
0.28
0.0090
4lai4
0.881
3
137.9
0.12357E
07
43. C9
C*32573E
03
0.21395E-02
0.465 E-04
21.
0.29
0.0093
42^06
0.937
4
143.0
0.12900E
07
43.03
0*14073E
04
0.18765E-02
0.454E-04
26.
0.28
0.0092
42*20
0.949
5
148.1
0.13443E
07
43. C5
0il9786E
04
0.178 7 4E- 02
0.450E-04
34.
0.29
0.0095
41*88
0.928
6
153.2
0. 13986E
07
43.07
0i25502E
04
0.16701E-02
0.444E-04
39.
0.31
0.0100
41A72
0.917
7
158.2
0.14 52 9E
07
43. C7
0i3l368E
04
0.16152E-02
0.442E-04
43.
0.29
0.0093
41i59
0,909
6
163.3
0.15073E
07
43.05
0i36811E
04
0.156536-02
0. 4416-04
46-
0.27
0.0087
42A46
0.964
c
168.4
0,15616E
07
43. C3
0A42181E
04
0.1A709E-02
0.43 8 E-04
49.
0. 27
0.0087
41 170
0.918
10
173.5
0.16159E
07
43.07
0*47267E
04
0. 1436 5E-02
0.4356-04
52.
0.30
0.0097
41A00
0.873
11
178.6
0.16702E
07
43.07
0452670E
04
0.13962E-02
0.434 E-04
55.
0.29
0,0094
40190
0.867
IZ
183.6
0. 17245E
07
43. C7
Qi57B48E
04
0.13624E-C2
Q.433E-04
58.
0.31
0,0100
40484
0.863
13
187.5
0. 17658E
07
42.61
0i63117E
04
0.137346-02
0.493E-04
59.
14
190.1
0.17938E
07
42.42
0*63509E
04
0.14227E-02
0.521E-04
59.
15
192.7
0. 13217E
07
42.73
0i63908E
04
0 .14254E-02
0.532E-04
59.
16
195.4
3. 18498E
37
^2. 73
0i643a6E
04
0.14326E-02
0.526E-04
60.
17
198.0
0.18780E
07
42. 73
0.64710E
04
0-143 5 8E-02
0.529E-04
60.
18
200.6
0.19059E
07
42.67
0.65111E
04
0.14332E-02
0.628E-04
60.
19
203.2
0.19339E
07
42.63
Oi655CSE
04
0. 14096E-02
0.513E-C4
60.
20
205.8
0.19619E
07
42.75
0.65906E
04
0.142276-02
0.522E-04
60.
21
203.5
0,19898E
07
42.73
G.66302E
04
0.14057E-C2
0.516E-04
60.
22
211.1
0.20178E
07
4 2.73
0466699E
04
0.14255E-02
0.527E-04
60.
23
213.7
0.20458E
J7
42. 71
G.67094E
04
D. 139796-02
0.5146-04
60.
24
216.3
0.20739E
07
42.86
0:674866
04
0 , 14019F-02
0.528E-04
60.
2 5
218.9
G.2102DE
37
42. 76
0i67880E
04
0.141086-02
0. 5246-04
60.
26
221,6
0.2130CE
07
42. 59
0 A68278E
04
0. 142946-02
0.553E-04
60,
27
224.2
0.21580E
07
41.61
0*68671E
04
0.13778E-02
0.474E-04
60.
23
226.8
0.21859E
07
42. 63
Ci69C64E
04
0.14325E-02
0.560E-04
60.
29
229.4
0.22139E
07
42.58
04694606
04
0 .139556- C2
0.506 E-04
60.
30
232.0
0.22419E
07
42. 9C
04698616
04
0.14636E-02
0.549E-04
60.
31
234.6
0.22698E
07
42.88
0 A70268E
04
0. 144536-02
U.53BE-04
60.
32
237.3
0.22979E
07
42. 65
0i70678E
04
0.14821E-02
0.542 E-04
60 •
33
239-9
0.23261E
07
42.63
0471093E
04
0. 148326-02
0.550E-04
60.
34
242.5
0.23540E
0?
42. 27
01715C4E
04
0.145096-02
0.522F-04
60.
35
245.1
0.23 820E
07
42.54
0471917E
04
0.15014E-02
0.571E-04
60.
36
247.8
0. 24100E
37
42.20
0472338F
04
0.15048E-02
0.624E-04
60.
UNCERTAINTY IN REX=27158. UNCERTAINTY IN F=0.C5036 IN RATIO
D^^
0.019
0.019
0.019
0.019
0.019
0.019
0.019
0.019
0.019
0.019
0.019
130
BUN
090374
DISCRETE HCLE RIG
444 NAS-3-
143
36
STANTON
NU'IBER
DA TA
444
2700STEP30
M«0.3 . TH
= C P/D=5
RUN
090474 ***
DISCRETE HOLE RI£
444 NA5-3-
14336
STANTON
NUMBER
DATA
444
2700STEP30
M=*0.3 TH
=1 P/D=5
LINEAR SUPERPOSITION I.S APPLIED TO STANTCN NUMBER
CATA FROM
RUN
NUMB BIS 090374 AND
J09 0474 TO OBTAIN STANTCN NUMBER CATA AT TH»0 AND
THal
PLATE
REXCOL RE
0EL2
ST(TH=0)
REXHOT
RE
CEL 2
ST(TH*1)
ETA
STCR
F-COL
STHR
f-hot
LDGB
I
1136091.0
99.7
0.003642
1127044.0
94.2
0.003469
UUUUU
1.040
0.0000
0.990
0. 0000
0.990
2
1190843.0
287.. 5
0.003219
1181359.0
259.7
0.002625
0*184
0.847
0.0093
0.936
0.0090
2.167
3
1245594. 0
458.4
0.003022
1235675.0
878.2
0.002051
01321
0.890
0.0094
0.779
0. 0093
2.063
4
1300345.0
621.5
0.C02934
1289990.0
1467.4
0.001812
0*382
0.930
0.0095
0.718
0.0092
2.014
5
1355097.0
779.9
0.0028 52
1344305.0
2080.6
0.001717
0*398
0.956
0,0095
0.702
0,0095
2.067
6
1409848.0
934.8
0. C02807
1398621.0
2684.8
0.001575
0*439
0.983
0.0093
0.661
O.D LOO
2.102
7
1464600.0
1087.3
0. .0027 64
1452936.0
3310.8
0.001506
0*455
1.005
0.0093
0.646
0.0093
2.021
B
1519351.0
1236.6
0. C02689
1507252.0
3895.7
0.001489
0*446
1.008
0.0094
0.651
0.0087
1.976
9
1574102.0
1382.4
0.002639
1561567.0
4445.6
0.001398
0*470
1,017
0.0095
0.622
0.0087
1.952
10
1628854.0
1527.4
0.C02655
1615662.0
4988.9
0.001294
0*513
1.049
0.0093
0.585
0.0097
2.052
11
1683605.0
167L.1
0.002595
1670198.0
5585.4
0.001217
0*531
1.047
0. 0093
0.558
0.0094
1.990
12
1738357.0
1809.5
0.00 2461
1724513.0
6161.7
0.001191
0*516
1.013
0.0093
0.553
0.0100
2.078
13
1779968.0
1911.0
0.002416
1765793.0
6756.2
0.001211
0*499
1.006
0.568
14
1808165.0
1978.3
0.002352
1793765.0
6791.1
0.001278
0*457
0.991
0.603
IB
1836362.0
2043.8
0.002285
1821738.0
6827.1
0.001291
0*435
0.971
0.613
16
1 £64695.0
2107-3
0., 0022 15
1849846.0
6863.5
0.001311
0*408
0.949
0. 625
17
1893029.0
2169.3
0.DQ2180
1877954.0
6900.3
0.001320
0*394
0.941
0.633
18
1921226.0
2230.2
O.C02136
1905926.0
6937.3
0.001324
0*380
0.929
0.638
19
1949423.0
2289.4
b..002059
1933899.0
6974.2
0.001308
0*364
0.902
0.634
20
1977620.0
2347.5
0.002053
1961871.0
7011.1
0.001324
01355
0.906
0.645
21
2005817.0
2405.3
0.002046
1989844.0
7047.9
0.001306
01362
0.909
0.639
22
2034014.0
2462.2
0.001987
2017816.0
7084.9
0.00133B
01326
0. 889
0.658
23
2062211.0
2518.1
0.001969
2045789.0
7122.0
0.001309
0*335
0.887
0.647
24
2090545.0
2573.7
0-001974
2073897.0
715 8.7
0.001313
0,335
0.895
0.652
25
2118879. 0
2629.3
0. 001965
2102005.0
7195.6
0.001325
0.326
0.896
0.660
26
2147C76.0
2684.6
0.001947
2129977.0
7233. 1
0.001349
0*307
0.893
0.675
27
2175273.0
2740.3
0. 002000
2157950.0
7269.9
0.001281
01360
0.923
0.644
28
2203470.0
2795.9
0.001939
2185922.0
73 06.8
C. 001354
01302
0.900
0.6B3
29
2231667.0
2850.8
0.001949
2213895.0
7344.1
0.001309
0*32 8
0.909
0.664
30
2259864.0
2905.7
0.001945
2241667.0
7381,8
0.001389
0*286
0.913
0.707
31
2288061.0
2960*6
0.001940
2269840.0
7420.4
0.001368
0. 295
0.915
0.699
32
2316394.0
3015.1
0.001923
2297948.0
7459.4
C.001413
0*265
0.911
0.725
33
2344728.0
3069.4
0.001922
2326056.0
7499.0
0.001415
0.264
0.916
0,728
34
2372925.0
3123.7
0.C01922
2354028.0
7538.1
0.001378
U12B3
0.920
0.712
35
2401122.0
3178.1
0.001938
2382001.0
7577.4
0.001433
0*260
0.932
0.743
36
2429315.0
3232.2
0.001693
2409973.0
7617.7
0.Q01444
0*237
0.915
0.751
STANTON NUMBER RATIO BfASEC ON ST*.PR*»0,4=0,029 5*REX**<-«2 II .-{XI /(X-XVD ) -1. /9. >
STANTON NUMBER RATIO FOR TH=1 IS CENVERTEO TO COMPARABLE TRANSPIRATION VALJE
USING ALCGd * B)/B EXPRESSIGK IN THE BLOWN SECTION
PUN 090474-1 OISCRETP HOLE RIG *** NAS-3- 14334
STAN ION NU^BEO DATA
M
U>
TACe=
26.3d
DEG C
UINF
=
16.63 M/S
TINF= 26.76
DEG C
RHC =
1. loO
K&/M3
V ISC
- 0.15751E-04 M2/S
XVC= 22.4
CM
CP =
IT 17. .
J/ KGK
PH=
Ca71B
27C0S7
'ER30 M=C
1. 3
TH=1.25
F/D=5
PLATE
X
REX
TO
FEENTH
STANTON NO
0S7
DREEN
M
F
72
THETA
DTH
1
127.8
D.11263E
07
43. 52
0190 11 5E
02
0.33205E-02
0.523E-04
1 .
2
132.3
0. L1806E
07
43.54
0.24816E
03
0 .25029E-02
C.473E-04
15.
0.26
0.0084
47,46
1.234
0.020
■a
137.9
0.12348b
07
43. 56
0.92537E
03
0.17805E-02
0.436E-04
27.
0.27
0,0087
48139
1.288
0.020
4
143-0
0.12891S
07
43. 58
0U6225E
04
0.147186-02
0.4246-04
35.
0,27
0.0086
48163
1.300
0.020
5
I'tS.l
0. 13434c
07
43.56
0i23Q82c
04
0.13638E-02
0.4 20E-Q4
42.
0.27
0.00B9
48117
1.2 75
0.020
6
153.2
0.13977E
07
43.56
01299356
C4
0. 12920E-02
0.416E-04
4B.
0.27
0.0088
48112
1.271
0.020
7
158.2
0.14519E
07
43,56
0 *366466
04
0.116716-02
0.414E-04
52-
0.25
0.0081
47184
1.255
0.02 0
B
163.3
0.15062E
07
43.56
Oi42797E
04
0.11297E-02
0.413E-04
57.
0.25
0.0081
49121
1.336
0.020
9
168.4
0. 15605E
07
43. 56
0149262E
04
0. 104246-02
0.411 E-04
61-
0.25
0.0082
48103
1.266
0. 020
10
173.5
0.16148E
07
43.58
0155424E
04
0. 10200E-02
0.409E-04
64.
0.2B
0.0091
47123
1.217
0.019
11
178.6
0.16^911:
07
43. 58
0161993E
04
0.95298E-03
0.478E-04
68.
0.27
0.0086
47103
1.205
0.019
12
183.6
0.17223c
07
43. 56
0i68119E
04
O.92013E-O3
0.408 E-04
71.
0.28
0.0090
46193
1.200
0.019
13
187.5
0.17646E
07
43.25
0174403E
04
0.10193E-02
0.392E-04
73.
14
190.1
0.17925E
07
43. 12
0J74701E
04
0.111186-02
0.426 E-04
73.
15
192o7
0.182O5E
07
43.35
0.75016E
04
0.11349E-02
0.439E-04
73.
16
195.4
0. 1848 6E
•07
43. 33
Q175337E
04
0.11577E-02
0.440E-04
73.
17
198.0
0.13767E
07
43.31
0175664E
04
0.11836E-02
0.449E-04
73.
18
200.6
0.19046E
07
43, 28
04759966
04
0-11833E-02
0.4506-04
73.
19
203.2
0.19326E
07
43.22
0.76327E
04
0.118556-02
0.442E-04
73.
20
205. 8
0.19605E
07
43.31
0176661E
04
0.12048E-02
0.452E-04
73.
21
208.5
0.1988 56
07
43.31
0W6995E
04
0.11777E-02
0.447E-04
73.
22
211.1
0.20164E
07
43.20
0i77331E
04
0.12246E-02
0.461E-04
73.
23
213.7
0.20444E
07
43. 16
0177672E
04
0.12147E-02
0,4546-04
73.
24
216.3
0. 20725E
07
43.39
OJ78009E
04
0. 11947E-02
0.466E-04
73.
25
218.9
0.21006E
07
43.22
0*78350E
04
0.123686-02
0.468E-04
73.
26
221.6
0.21285E
07
43.03
0478700E
04
0.12627E-02
0.492E-04
73.
27
224.2
0.21565E
07
42- 25
0179042E
04
0. U854E-02
0.422 e-04
73.
28
226.8
0.21844E
07
43.14
0179384E
04
0.12561E-02
0.500 E-04
73.
29
229.4
0. 221246
07
43oC3
01797326
OA
0.123A0E-C2
O.A57E-OA
73.
30
232.0
0.22403H
07
43.22
C 1800916
04
0.13296E-02
0.5016-04
73.
31
234.6
0.22683E
07
43.26
01804576
04
0.12862E-02
0.490 E-04
73.
32
237.3
0.22964E
07
42.95
0180825E
04
0 .134226-02
0.495E-04
73.
33
239.9
0.23 24 5E
07
42. 97
Ci81198E
04
0.13226E-02
0.500 E-04
73.
34
242-5
0.23524E
07
42.73
0181567E
04
0.13139E-02
0.480E-04
73.
35
245.1
0.23804E
07
42.86
0*819416
04
0.13651E-02
0.524E-04
73.
36
247.8
0.24083E
07
42.59
0182322E
C4
0- 13533E-02
0.566E-04
73.
UNCERTAINTY IN R.EX=2113?.
UNCERTAINTY IN F=C.05037 IN RATIO
132
RUN
C80174-1 DISCRETE HCLE
RIG *5^* NAS -3-
14 336
STANTON NUMBER DATA
TADS=
25.96
DEG C
U INF
' 3
16.87 M/S
TINF= 25.63
DEG C
RHC =
1.176
KG/M3
Vise
- 0.15539E-04 P2/S
XVC= 22,4
CM
CP =
10 14.
J/KGK
PR=
0i7l6
2700STEP40 M=(
3.4
TH=0
P/0=5
PLATE
X
REX
TO
R5ENTH
S7AMCN NO
CST
DRE6N
M
F
T2
THETA
DTH
1
127.8
0.11441E
07
38. CO
0a99 211E
02
0,360228-02
0.7136-04
2,
2
132. 8
0,11993E
07
27, S6
Oi28488E
03
0.312865-02
0.6776-04
10,
0.42
0.0135
26i02
0,015
0.026
3
137.9
0. 12 5440
07
37.92
Go46447£
03
0.297358-02
0.6676-04
17.
0.40
0,0129
26o31
0.040
0.025
4
143.0
0.13C95E
07
27. S4
0i65318E
03
0.28453E-02
0.6576-04
21 .
0.41
0.0133
26i23
0.033
0.025
5
148.1
0.13647E
07
=7,94
0683096E
03
0, 273318-02
0.649S-04
25 .
0.40
0,0129
26^21
0.031
0.025
6
153.2
0.14198E
07
37. S4
0il0028t
04
0.26999E-02
0.647E-04
28.
0.40
0.0131
26*23
0.032
0.025
7
158.2
0.14750E
07
27. S2
Cill7426
04
0.26709E-02
0.6466-04
31-
0.40
0.0129
26i36
0.044
0.025
8
163.3
0.153Q1E
07
37.92
0.13511fc
04
0. 26193E-02
0.6426-04
34.
0-41
0,0132
26*36
0.043
0.025
9
168.4
0.168S2E
07
27.58
Oil 52576
04
0.25694E-02
0. 6366-04
37-
0.40
0.0130
26*35
0.042
0.025
10
173.5
0, 16404E
07
37,96
Oil6976E
04
0.25639E-02
0.6366-04
39,
0.40
0.0129
26.32
0.040
0.025
11
178.6
0.16955E
07
27.98
flil8666E
04
0.25255E-02
0.6336-04
41 .
0.40
0.0129
26*37
0.044
0.025
12
183.6
0.17507E
07
38. 02
0120335E
04
0.239066-02
0.6226-04
43.
0.39
0.0128
26*36
0.043
0.02 5
12
187.5
0. 17S26E
07
27,24
C&21639E
04
0.238116-02
0.820E-04
44 o
14
190.1
0.18210E
07
37.18
Oi222S8E
04
0.255446-02
0. 8186-04
44.
15
192.7
0- 18494E
07
27. 52
0A22S3ie
04
0.219896-02
0,8086-04
44.
16
195.4
0.18779E
07
37.58
0i23548E
04
0.. 2 14 3 5c- 02
0.780E-04
44.
17
198.0
0.19064E
07
27.64
0<i24151E
04
0,209756-02
0.7686-04
44.
18
200.6
0,193486
07
27. 62
0^247436
04
0,206776-02
0.757E-04
44.
IS
203.2
0.19632E
07
37,60
0i25322E
04
0.2C088E-02
0.729E-04
44.
2C
205.8
0. 19916E
07
27. 71
0i25892E
04
0.159458-02
0. 7306-04
44.
21
208o5
0.20200E
07
37,71
0b26453E
04
0.195676-02
0.7136-04
44.
22
211.1
0. 20484E
07
27. £1
0*27002E
04
0.190566-02
0,7106-04
44,
23
213.7
0.207686
07
37.77
0127539E
04
0. 166606-02
0.6886-04
44.
24
216.3
0.21O53E
07
37.90
0i280716
04
0.187856-02
0.7066-04
44.
25
218.9
0.213396
07
37. £3
C.28607E
04
0.1 69056-02
0.6976-04
44.
26
221.6
0.21623E
07
27.87
Ci29142t
04
0. 187306-02
0.707E-04
44.
27
224-2
O.21907E
07
37c 54
01296956
04
0.201826-02
0.7256-04
44,
28
226.8
0,221916
07
37. 89
0i302376
04
0.179236-02
0.6856-04
44.
29
229.4
0.22475E
07
27. 75
Oi3074SE
04
0.180996-02
0.6586-04
44.
30
232.0
0.22 75 86
07
38. 10
0.312666
04
0.182536-02
0.6936-04
44.
31
234.6
0.230426
07
38.06
0.317826
04
0.161736-02
0.677 6-04
44 «
32
237.3
0.233286
07
37.96
0.3229SE
04
0. 17999E-02
0,6736-04
44.
32
239,9
0.236136
07
37.92
0.323116
04
0.ie067E-02
0.6806-04
44.
34
242.6
0.238976
07
27. t6
01333226
04
0.17971E-C2
0,6546-04
44.
35
245.1
0.241816
07
27.87
G.33836E
04
0. 180706-02
0.6996-04
44-
36
247.8
0,244656
07
27, £8
01343436
04
0.17632E-02
0.7496-04
45 .
UNCERTAINTY Hi REX=2756?. UNCERTAINTY IN F=0.J5335 IN RATIO
RUN 08017V2 DISCRETE HOLE RIG NAS-3-14336
S^ANTO^! number data
T4CB =
2 7,38
DEG C
UINF
=
16.81 M/S
TTNF= 27.26
OEG C
PHO =
1. 169
KG/M3
VI 3C
= 0.15668E-04 M2/S
XVC= 22,4
CM
CP =
1015,
J/KGK
PR =
01716
»**
27C0STEP4U M=C
).4
TH = 1
P/D=5 +
PLATE
X
REX
TC
FEcNTh
STANTCN NO
DST
0RE5N
M
F
72
THETA
OTH
1
127,8
0. 11310c
07
43.52
C .39313E
02
0. 227735-C2
0.532E-C4
2 .
i
132.8
O.ii 855E
07
43.62
Oi 25 211E
03
0.269636-02
0.4936-04
17.
7.38
0.0124
41175
0.886
0.019
3
137.9
0. 124D0E
07
43. 5t
C.*98511C
02
0.2203 8E- 02
0 .467 E-04
29.
0.37
0.0118
42i95
0.963
0.019
4
143.0
0.12945E
07
43.58
0.17150E
04
0. ie070£-02
0.448E-04
38.
0.37
0.0121
43^68
1.006
0.019
5
148.1
J.1349JE
07
43.56
Oi24704E
04
0.16427E-02
0.441E-04
45 .
0.37
0.0119
42.93
0.960
0.019
6
153.2
U. 1'4035£
07
43.58
C.31782E
04
0.15277E-02
0.436E-C4
51.
0. 38
0.0122
42i86
0.956
0.019
1
158,2
0. 14580E
07
43. 60
0*389316
04
0.146595-02
0 .4336-04
57,
0.37
0.0120
42*50
0.933
0.019
8
163.3
0.15125E
07
43.60
0*458466
04
0.14484F-02
0.423E-04
61.
0.36
0.0118
43.07
0.968
0.019
<9
168.4
0. 156706
07
43.58
C.52817E
04
7.13812E-02
0.4316-04
66.
3.37
o.oua
42*32
0.923
0.019
10
173.5
0, 16215E
07
43.56
0*59519F
04
0.1254 1E-C2
0.430e-C4
69,
0.36
0.0 117
41.41
0.868
0.019
II
178.6
Q.167b0t
07
43.54
0.65787E
04
0 .121255-02
0 .4295-04
73 .
0.38
0,0123
4l;05
0.847
0.019
12
183.6
0.17305E
07
43.54
0*721316
04
0.127846-02
0.428E-04
76.
0.37
0.0119
40-52
0.814
0.018
13
187.5
0. 17719E
07
42.55
0177993E
04
0.12314E-02
0.4466-04
77.
14
190,1
0. 18 0,00£
07
4 2.78
C178341E
04
0.12471E-C2
0. 4715-04
77.
15
192.7
0.18281E
07
43. C5
0*7B692E
04
0 .124966-02
0.479E-04
77.
16
195.4
0. 1856 3E
07
43.05
C 179043E
04
0. 12456E-02
0.471 E-04
77.
17
198,0
0.18845E
07
43.05
0*793936
04
0.12449E-02
0.471E-04
77,
10
200.6
0. 19126E
07
4 3.03
0*797416
04
0.12320E-02
0.468 E-04
77.
19
203.2
0- 194Q6E
07
43. Cl
01800345
04
0. 12121E-02
0.454E-04
77.
20
205.6
0.19687E
07
43. 12
01804246
04
0.12066E-02
0.4576-04
77.
21
208.5
0.19968E
07
43. C9
C. 807636
04
Q.12061S-C2
0. 455E-04
77.
22
211.1
0.20248E
07
43.09
0.81102E
04
0. 12038E-02
0,461E-04
77.
23
213,7
0.20529E
07
^3.C7
0181437E
C4
0.11802E-02
0.450 E-04
77.
24
216.3
Q.20B115
.07
43.18
0i81770F
04
0.11921E-02
0.4646-04
77.
25
218.9
0.21093E
07
43. 11
C182105E
04
0. 119396-02
0.458E-04
77.
26
221.6
0.21374E
07
43.03
0 *82446F
04
0.12354E-02
0.474E-C4
77.
27
224.2
0.21655E
37
42. 82
C*32803E
04
0.130436-02
0.483E-04
77.
2B
226.8
0.21935E
07
43.09
0.33L52E
04
0. 11748C-02
0.462 E-04
77.
29
229.4
0.22216E
07
42. 54
C*83483E
04
0.11810E-02
0.442E-04
77.
30
232.0
0.2249 7E
07
43. 18
C.83822E
04
0.L2367E-02
0.479E-04
77.
31
234.6
C.22777E
07
43.18
C*84168t
04
0.122556-02
0.472E-04
77.
32
237.3
C.23059E
07
42. 99
Qi845I6£
04
0.12455E-Q2
0.473E-04
77.
33
239.9
0.23341E
07
42.95
0.84867E
04
0 .1254eE-02
0.480E-04
77.
34
242.5
0.23622E
07
42.73
0*852166
04
0.12330E-02
0.459E-04
77.
35
245.1
0.23903E
07
42. 86
0 *055686
04
0.12718E-02
0.501E-04
77.
36
247.8
0. 24184E
07
42. 56
0185922E
04
0.12476E-02
0.540 E-04
77.
LNCERTAIMTY IN REX=27252. UNCERTAPNTY IN F=0. 05036 IN RATIO
PUN
0BO17A-1 «<-»■ OISCKETE HCLP RIG *-'* NAP-3-lA33^
STANTON Nl.HP^P
DATA
*** 2700STEP4U «=C.A.
th=c
p/0=5 **•«
RUN
08017A-2 +»* CISCRtTE HOLE RIG *»* NAS-3-1A33C
STANTON NUMBER
DATA
*♦+ 2700STFF43
TH=1
P/C=5
LINEAR SUPERPOSITIDN IS APPLIED TC STANTON NU'^ t-P lATA fPOM
RUN NUMBERS 080i7A-l AND C3G17A-2 TO 0&TAI^. SPANTCN NUMBER
PfTA AT TH = 0 AND
th = 1
PLATE
PEXCGL
RE DEL2
3T( Th = 0 I
REXHOT
RE DEL 2
ST(TH=n
ETA
STCR
•=-: CL
S'^HR
P ■ HOT
L0G3
1
1144127.0
99. 3
0, 003602
1130962.0
89.3
0.003277
UUUUJ
1.028
0. 0000
0.936
0.0000
0.936
2
1199266.0
235 . 1
0 .00 3136
1185467.0
250.6
0.002640
0.158
0. 825
0. 01 35
0.943
0.0124
2.543
3
1254405. 0
454.2
0.C02997
1239971.0
1057.3
0.002139
0.286
0.883
0.0120
0.812
0.0 118
2.394
4
1309544. 0
616.3
0.CO28E 5
1294475 .0
1800.9
0.001790
0.3B0
0.915
0.0133
0.709
0.0121
2.334
5
1364682.0
772, 2
0. C02770
1 346979.0
2559.3
0.00162 3
3.414
0.929
■0 . 0 1 2.9
0.66 3
0.0119
2. 291
6
1419821.0
924.1
0. 002740
1403484.0
3290. 8
0.001475
0.462
0.960
0.0131
0.619
0.0122
2.293
7
147496C.0
1074.7
0. C02722
1457988.0
4031.6
0i489
0.989
0.0129
0.597
0.0120
2.277
8
1530098.0
1223.5
0. C0267 5
1512492.0
476 3.4
10.001384 1
0.493
1.004
0.0132
0.605
0.0 118
2.2 84
9
1585237. 0
1369,7
0.002626
1566996.0
5477.4
C. 001309
OiSOl
1.012
0.0130
0.582
0.0118
2.283
10
1640376.0
1514.3
0.C02623
1621500.0
6191.3
C. 001206
0.540
1.036
0.0129
0.545
0.0117
2.231
11
1695514. 0
1658 .0
1676005.0
6892.4
C. 001101
0.575
1.045
0. 0129
0.504
0. 0123
2.258
12
1750653.0
1797 .0
173C5C9.0
7622.3
0.001039
0.576
1.010
0.0128
0.48 2
0.0119
2.193
13
1792559.0
1899 .3
0. C02445
177 1932.0
8314.1
C. 000984
0. 598
1.021
0.461
14
1820955. 0
1966.9
J. C02310
1800002.0
8342.4
0.001030
0.554
0.973
0.486
15
1649351.0
2031 .8
0. 002252
1828072.0
6371.6
0.001045
0.536
0.957
0.496
16
1677885.0
2 C 95.0
0.002193
1856277.0
8401.1
0.001052
0.520
0.9 40
C.502
17
1906420. 0
2156 .6
0.002145
1884483.0
8430.8
0.001061
0.505
0.927
0.509
18
1934816.0
2217.2
0.002114
1912553.0
E460.5
0.001052
0.502
0.9 20
0.507
19
1963213.0
2276.4
0.C02053
1940623.0
£489.9
0.001041
0*493
0.900
0.504
20
1991609.0
2334.6
0.002038
1968692.0
6519. 1
0.001037
0*491
0.900
0.505
21
2020006.0
2392.0
0.CQ1998
IS96762.0
6548.3
0.001045
0.477
0.889
0.511
22
204B402.0
2448.0
0.001945
2024832.0
6577.6
0.001053
0.459
0.871
0.51S
23
2C76799.0
2502.8
0. 001906
2052902.0
8607.1
0.001032
0*459
0.^9
C.510
24
2105332.0
2557.1
0.001917
2081107.0
6636.3
0.001044
0*455
0.869
0.518
25
2133867. 0
2611 .8
0. 001929
2109313.0
8665.6
0.001044
0*459
0.880
0.520
26
2162263.0
2666 .3
O.C019C8
2137383.0
8695.7
0.001098
0*425
0.876
0.550
27
2190660.0
2722.7
0.002058
2165452-0
6727.3
0.001151
0*441
0.9 50
0.578
28
2219056.0
2777-9
0.001827
2193522.0
£75 8.1
0.001042
0.430
0.048
0.526
29
2247453. 0
2830.1
0.001845
2221592.0
8787-5
0.001046
0*433
0. 861
9.530
30
2275649.0
2882.7
0. 001858
2249662.0
£817.8
0.001110
0*403
0.872
0.565
31
2304246. 0
2935.5
0.C01650
2277732.0
6848. B
C. 001098
0*406
0.073
0.561
32
2332780.0
2987.8
0.001831
2305937.0
6680.0
0.001126
0.385
0.868
0.577
33
2361314-0
3039.9
0.001840
2334143.0
8911.0
0.001135
0*383
0. 877
0.584
34
23B9710. 0
3092.1
0.001828
2362213,0
8943.4
0.001112
0*392
0.876
0.574
35
2418107.0
3144.2
0.001837
2B90282.0
6975.2
0.001157
0*370
0.884
0.599
36
2446503. 0
3195.8
0.001792
2418352.0
9007.5
0.001137
0*366
0.866
0.591
STANTON NUMBER RATIO BASED ON ST*PR**0- A«0.0295*REX** (-.2 I ♦ <1 (X 1/ ( X-XVO II **0.9 ) »♦( -I ,/9. )
STANTON NUMBER RATIO FOR TH«1 IS CCNVERTED TO COMPARABLE TRANSPIRATION VALUE
USING ALOGd * 6)/B EXPRESSION IN THE BLOWN SECTION
135
RUN 080574 *** DISCRETE HOLE RIG NAS-3-14336 STANTON NUMBER DATA
TACE»
27.67
OEG C
UINF
■ =
17.12 M/S
TINF* 27.54
OEG C
PHOv
1. 168
KG/M3
V ISC
> 0.15699E-04 M2/S
XVO= 22.4
CM
CP*
1015.
J/KGK
PR»
Oi716
***
2700STEP60 M-C
1.6
TH=0
P/D*5
PLATE
X
REX
T0“
PEE NTH
STANTON NO
OST
OREEN
M
F
T2
THETA
OTH
1
127.8
0.1149 7 E
07
39.39
Oi95295E
02
0.34398E-02
0.712E-04
2.
Z
132.8
0.12 05U
07
39.37
0A27748E
03
0.31364E-02
0,6896-04
14.
0.58
0.0189
2BiZ6
0.060
0 .02 6
2
137.9
0. 12605E
07
39.37
Ci51479E
03
0.31420E-02
0.689E-04
24.
0.58
0.0188
28141
0.073
0.026
4
143.0
0.13159E
07
39. 39
C476200E
03
0.3C325E-02
0.680E-04
31.
0.57
0.0184
28141
0,073
0.026
5
148.1
0.13713E
07
39.39
0^10006E
04
0.2899 66-02
0.670E-04
36.
0.56
O.OIBI
2BL38
0.070
0.026
6
153.2
0. 1426 7E
07
39. 39
0A12291E
04
0.2E067E-02
0.663E-04
41.
0.58
0.01B9
28146
0.077
0.026
7
158.2
0.14821E
07
39.41
0A14655E
04
0.280036-02
0.661E-04
45.
0. 59
0.0189
28159
0.088
0.026
6
163.3
0.15375E
07
39.39
01171206
04
D.27594E-02
0.6596-04
49.
0.58
0.0189
28165
0.093
0.026
9
168.4
0.15929E
07
39.39
01196116
04
0. 27067E-02
0. 6565-04
53.
0.57
0.0186
28172
0.100
0.026
10
173.5
0.16484E
07
39.39
Q*22142E
04
0.27237E-02
0.657E-04
56.
0.57
0.0185
26168
0.096
0.026
11
178.6
0.17038E
07
29.37
0l24621E
04
0.2681EE-02
0.6555-04
60.
0.57
0.0186
28190
0.115
0.026
12
183.6
0. 17592E
07
29.39
0127276E
04
0.26299E-02
0.650E-04
63.
0.57
0.01B6
28187
0.112
0.026
13
187.5
0.18013E
07
28. 89
C429529E
04
0.25950E-02
0.900E-04
64.
14
190.1
0.1829EE
07
38.95
0130241E
04
0.23908E-02
0.866E-04
64.
15
192-7
0.18583E
07
39.29
0130918E
04
0.23442E-02
0.855E-04
64.
16
195.4
0.18870E
07
39.37
0131575E
04
0.2258ZE-02
0.8165-04
64.
17
198.0
0. 19157E
07
39.46
0132211E
04
0.21968E-02
0.799 E-04
64.
18
200.6
0.19442E
07
39.48
0132832E
04
0.2150JE-02
0.7825-04
64.
19
203.2
0.19728E
07
39. 50
C133437E
04
0.2C806E-02
0.752E-04
64.
20
205.8
0.20013E
07
39.62
0.3402 8E
04
0.20593E-02
0.750E-04
64.
21
20 8.5
0.2029EF
07
39.60
0134610E
04
0.20161E-02
0.731E-04
64 ..
22
211.1
0.20584E
07
'39.69
0135179E
04
0. 156656-02
0.7275-04
64 .
23
213.7
0.2C869E
07
29. 67
Cfc35732E
04
0.190476-02
0.699E-04
64.
24
216.3
0.2115ee
07
29. ei
0.36277E
04
0.191036-02
0.7126-04
64 .
25
218.9
0.21442E
07
39.79
0136618E
04
0,187556-02
0.692E-04
64.
26
221.6
0.21728E
07
29.82
0.37354E
04
0.188015-02
0.708E-04
64.
27
224.2
0.22013E
07
39.48
0;37909E
04
0. 200455-02
0.7156-04
64.
28
226.8
0.22 298E
0 7
39.92
0.38450E
04
0. 178136-02
0.6836-04
64.
29
229.4
0.225846
07
39. 73
0.38958E
04
0.177555-02
0.643E-04
64,
30
232.0
0.22E69E
07
40. 11
0139466E
04
0. 177935-02
0.676 E-04
64.
31
234.6
0.23155E
07
40.11
0139970E
04
0. 174935-02
0.656E-04
65.
32
237.3
0.23441E
07
39-98
01404686
04
0.173686-02
0.649 E-04
65.
33
239-9
0.23728E
07
29. 94
014096 =E
04
0.17321E-02
0.652E-04
65.
34
242.5
0.24013E
07
39.71
C.41455E
04
0. 17139E-02
0.62 76- 04
65.
35
245-1
0.24299E
07
39.92
Cl41S46E
04
0.171 745-02
0. 6675-04
65.
36
247.8
0.24584E
07
39.65
0142429E
04
0.166645-02
0.711E-04
65.
LNCEPTAINTV IN P-EX=277C3. UNCERTAINrv lA F*0. 05334 IN RATIO
RUN 08117^1 DISC RE T5 HCLE RIE ♦** NAS-3-14336
STANTON NUMBER DATA
!-*
U)
CT>
TAOB»
26.90
DEG C
UINF
=
17.05 M/S
TINF= 26-77
DEG C
RHO*
1.167
KG/M3
Vise
= 0.15669E-04 M2/S
XVO= 22-4
CM
CP =
1015-
J/KGK
PR=
0*717
2 700STEP60 M=0
1. 6
X
II
P/C45 ***
PLATE
X
REX
TO
REENTH
STANTON NO
DST
DREEN
M
F
T2
THETA
DTH
1
127.8
0-11473E
07
40.70
0i92461£
02
0.33445E-02
0.609E-04
2.
2
132.8
0-12026E
07
40.68
Ci26118E
03
0,275866-02
0.569E-04
23.
0.53
0,0173
38123
0.824
0-022
3
137.9
0.12579E
07
40.68
0ill936E
04
0.25335E-02
0.555 E-04
39,
0,53
0-0171
38156
0.848
0.022
4
143.0
0. 131i32E
0 7
40-70
0421262E
04
0.21633E-02
0.533E-04
51.
0,53
0.0171
3912 5
0-896
0-022
5
148.1
0. 13604E
07
40. 70
0i30887E
04
0 .19505E-02
0.5226-04
61-
0. 52
0.0168
39A29
0.899
0.022
6
153-2
0.14237E
07
40.70
0*402816
04
0-1E043E-02
0.515E-04
70.
0,52
0.0170
39149
0.913
0-022
7
158-2
0. 147S0E
07
40.72
0 i49 83 8E
04
0.17563E-02
0.512E-04
78.
0. 53
0.0172
39*64
0.922
0-022
e
163.3
0. 15343E
07
40. 70
0-59537E
04
0.16617E-02
0.508E-04
85.
0,53
0.0172
40102
0.951
0-022
9
168 .4
0.15896E
07
40.70
Oi69457E
04
0.1S815E-02
0.5056-04
92.
0.51
0.0166
39*80
0.935
0-022
10
173.5
0.164.49E
07
40.68
0*78B96E
04
0,1515£E-02
0.503E-04
98.
0.51
0.0164
39136
0.905
0-022
11
178-6
0.17002E
07
40.68
0.87937E
04
0- 14745E-02
0.501E-04
103.
0.52
0.0168
39.22
0-895
0.022
12
183.6
0. 17555E
07
40.68
0497040E
04
0- 14402E-02
0.500E-04
lOB.
0.52
0.0169
38191
0-873
0-022
13
187.5
0.17975E
07
40.26
0il0579E
05
0. 1447 3E-0 2
0.523E-04
111.
14
190.1
0- 18260E
07
40.24
0ilO62OE
05
0.13952E-02
0.534E-04
Ill .
15
192.7
0. 18545E
07
40.55
0410660E
05
0. 13762E-02
0.530E-04
111.
16
195.4
0.1803 IE
07
40. 50
0a0698E
05
0.13485E-02
0.513E-04
Ill .
17
198-0
0.19117E
07
40.64
0410736E
05
0.131856-02
0.506E-04
lll-
18
200.6
0. 19402E
07
40.64
0il0774E
05
0.129 5 7E-02
0.499E-04
111.
19
203.2
O.19606E
07
40.64
oiioaioE
05
0.12602E-02
0.479 E-04
Ill .
20
205.8
0.19971E
07
40.77
0.10846E
05
0.12438E-02
0.479E-04
111.
21
206.5
0.20 256 E
07
40.77
0410881E
0 5
0.12089E-02
0.466E-04
Ill .
22
211-1
0.2054 IE
07
40.81
0 410 915E
05
0-11891E-02
0.469 E-04
111.
23
213-7
0- 2082 5E
07
40. 79
3-10948E
05
0.11629E-02
0.456E-04
111.
24
216.3
a.21111E
07
40.93
0-10982E
05
0. 11586E-02
0.466F-04
111.
25
218.9
0.21 3,9 BE
07
40.89
0ai0l4E
05
O.H534E-02
0.456 E-04
111.
26
221.6
0.21682E
07
40. 89
0*11048E
05
0.1165CE- 02
0.466E-04
111.
27
224.2
0.21967E
07
40.68
CillOBlE
05
0-12120E-02
C.465E-04
111.
28
226.8
0.22252E
07
40. 98
0*11114E
05
0.H082E-02
0.454E-04
Ill .
29
229.4
0.2253 7E
07
40.05
0 *111466
05
0.10917E-02
0 .4 26 6-04
111.
30
232.0
0-22821E
07
41.12
0*11177E
05
0- 111 72E-02
0.456E-04
111.
31
234.6
0.23106E
07
41.10
0;11209E
05
0.110516-02
0. 4446-04
111.
32
237.3
0.23392E
07
40.98
Q111240E
05
O.llJOlE-02
0.443E-04
111.
33
239.9
O.23670E
07
40.94
0ai272E
05
O.U097E-02
0.4466-04
111.
34
242,5
0.23963E
07
40. 76
0*11303E
05
0.1C909E-02
0.427E-04
Ill .
35
245.1
0.2424EE
07
40. 89
0*11335E
05
0. 11050E-02
0.462E-04
Ill .
36
247.8
0.24 53 3E
07
40.64
0411366E
05
0.10664E-02
0.491E-04
111.
UNCERTAINTY IN REX=27645.
UNCERTAINTY IN F=0. 05034 IN RATIO
137
RUN
C80574
DISCRETE
HCLE
RIG
+♦* NAS-3- 14 236
STANTON
NIMBER
DATA
♦♦♦
2700STEP60 ^=C.6
TH=0
P/0*5
+++
PUN
08117 4-1
DISCRETE
HCLE
RIG
+ +♦ NAS-3-1433t
STANTON
NUMBER
DATA
2700STEP6D M=0.6
TH=l
P/D=5
LINEAR 3UPERPCS1TICN IS APPLIEC
TO STANTCN NUMBER DATA
FROM
PUN NUMBERS 080574 AND C81174-1 70 OBTAIN STANTCN NUMBER DATA A7 TH=0 AND TH=1
PLATE
REXCOL
RE 9EL2
STI TH=Ol
RE XHOT
PE CEL2
STITH=1 >
ETA
STCR
F-COL
STHR
= -HOT
.365
1
1149692.0
95. 3
0. 005440
1 147284.0
92.5
0.003345
UUUUU
0.982
0.0000
0.955
0.0000
0.955
2
1205099.0
278.3
0. 003166
1202574.0
258.8
0.002671
0.156
0.834
0.0189
0.958
0.3173
3.079
3
12605C6. 0
454.5
0.003195
1257865.0
1353-1
0.002404
0.248
0.942
0.0188
0.916
0.0171
3.115
4
1215913.0
629,3
J.C03112
1313156,0
2422.4
0. C02024
0.350
0.989
0.0184
0,804
0.0171
3.027
5
1371320.0
798.1
O.C02982
1366447.0
3476. C
C. 001833
0.385
1.002
0.0181
0.751
0.0168
2.972
6
1426727.U
960.9
0, C02896
1423738.0
4503.C
C. 001691
0.416
1.016
0.0189
0,712
0.0170
2.975
7
1482134. 0
1121.6
0.002904
1479028.0
5534.1
0.001654
0.431
1.057
0. 0189
0,711
0.0172
3.037
9
153754J.0
1281. 7
0.C02677
1534319.0
6572.6
0.001580
0.451
1.081
0.0189
0.693
0. 0172
3,043
9
1592947.0
1440 ,0
0.C02fc37
1589610.0
7606.6
C. 001506
0,469
1.095
0.0186
0.672
0. 0166
2.978
n
1648354. 0
1598.1
0. C02667
1644901.0
6604.4
0.001399
3.512
1.134
0.0185
0,634
0.0164
2.923
11
1703761.0
1756.2
■ 0.0Q2B4Z^
1700192.0
95 66.9
0.UJ1323
0* 534
1.149
0.01 86
0.60B
0.3168
2.947
12
1759168. 0
1912 .7
1 0.C02805I
1755482.0
10565.4
0.0)1261
0.550
1. 157
0.0186
0,587
0.3169
2,950
13
1801277.0
2029.9
0 .00276 4
1797503.0
11572.1
C. 001274
0*539
1.156
0.599
14
1629612. 0
2105.6
0.002533
1325978.0
U6C8.0
C. 001245
0.509
1.071
0.589
15
1653346.0
2177.4
0, CC2487
1654453.0
11643.3
C. 001230
0.505
1.058
0.5B5
16
1 667019.0
2247 . 1
0.002392
1883066.0
116 7 6. 1
0.001211
0.494
1.027
0.580
17
1915692.0
2314.5
0.002326
1911679.0
I 1712.3
C. 001186
0.490
1.006
0.571
18
1944227. 0
2380.2
0,002276
1940153.0
11745.9
0.001167
0.487
0.992
0.565
19
1972761.0
2444.2
O.C02202
1966620.0
11778.7
0.001137
0.484
0.967
0.553
20
2C0L296.0
2506.7
0.C02179
1997103,0
11810.9
C. 001121
0.436
0.964
0.548
21
2029831.0
2568.4
0.002125
2025578,0
11842.4
0. 001087
0.491
0.951
0.534
22
2053365.0
2628 .6
0.C02O81
2054053.0
1 18 7 3 . 1
C. 001072
0.435
0.933
0.529
23
2C869U0.0
2687.1
D.C02014
2C82527.0
119C3.4
C. 001051
0.478
0.909
0.521
24
2115573.0
2 744.7
J. 002021
2111140.0
1 1933. 3
0.001045
0.483
0.918
0.521
25
2144246. 0
2801 .9
J.C01982
2139753.0
11963. 1
0. 001)45
0.473
0.906
0,522
26
2172780.0
2858.6
0.00198(3
2168228.0
11993. C
0.001057
0.463
0.913
0.531
27
2201315.0
2917.2
0.002121
2196703.0
12023.7
0. J01O92
)*485
0,981
0.551
23
2229849.0
2974.4
0. ccieao
2225177.0
12053.6
C. 001007
0.4o5
0.874
o;5io
29
2258364.0
3028.1
0.C01876
2253652.0
12082.1
C. 000989
0.473
0.877
0.503
3J
2286919.0
3C31.7
0. C01677
2282127.0
12110.6
0.001017
0.453
0.362
0.519
31
2315453,0
3134.3
0.C01844
2310602.0
12139,5
C. 001008
0.453
0.871
0.517
32
2344126. 0
3187.3
J.C01E31
2339215.0
12168.2
C. 001004
0.451
0.369
0.517
33
2372799. 0
3239.5
0. C01824
2367828.0
12197.0
C. 001016
0 .443
0.870
0.525
34
2401334.0
3291.4
0. C01606
2396302.0
12225.7
C. 000997
0,443
0.066
0.517
35
2429860. 0
3343 .0
0.CO18C8
2424777.0
12254.3
C, 001013
0.440
0.871
0.527
36
2458403. J
3393.9
3.CC1755
2453252.0
12262.7
C. 000976
0i444
0,849
0.509
STANTCN NUMBER RATIO HASEC ON ST+PR** C , 4= 0. 029 5*R£ >♦* (-. 21 * < 1 .- ( X 1/ ( X-XV 0 )) +*0.9 I ♦* (-1, /9 . )
STANTON riJRRER RATIO FDR 7H= I IS CONVERTED TO CCMPAPABLE TRANSPIRATION VALUE
USING ALCCa + 6)/b EXPRESSION IN THE BLOWN SECTION
RUN 061574-1 **■* DISCRETE HOLE RI€ *** NAS-3-^ 14336
STANTCN NUMBER DATA
TACfr*
26.88
DEC C
UINF
as
17.12 H/S
TINF* 26.75
DEG C
RHOp
1.166
KG/M3
Vise
* 0.15689E-04 M2/S
XVO* 22.4
CM
CP*
1015.
J/KGK
PR =
0J717
***
2700STEP75 M=0.?5
TH«0
F/e»5
PLATE
X
REX
TO
REENTH
STANTCN NO
DST
DREEN
M
F
T2
THETA
OTH
1
127.8
0.11504E
07
37.22
Oi99736E
02
0.35979E-02
0.815E-04
2.
2
132.8
0.12 0586
07
37. 16
Oi28746E
03
0.31739E-02
0.781E-04
21.
0.77
0.0250
26^72-
>0.003
0.030
3
137.9
0. 1261 3E
07
37.22
0A46340E
03
0.33393E-02
0.791E-04
36.
0,76
0.0245
26190
0.014
0.030
4
143.0
0.13167E
07
37.24
Ci66733E
03
0.332656-02
0.789E-04
46.
0.77
0.0250
26192
0.016
0.030
5
148.1
0.13722E
07
37.24
0i869S4E
03
0. 31859 E-02
0.777E-04
54.
0.76
0.0246
26^89
0.013
0.030
6
153.2
0.14276E
07
27. 22
Ca06l8E
04
0.312 686-02
0.773 E-04
62.
0.76
0.0247
26191
0.014
0.030
7
158.2
0.14831E
07
27.22
0112546E
04
0.31096E-02
0.772E-04
68.
0.76
0.0246
27102
0.025
0.030
8
163.3
0.153'85E
0 7
37. 24
0il4591E
04
0.30245E-02
0.763E-04
74.
0.77
0.0251
17*07
0.030
0.029
9
168.4
0.15939E
07
37.22
0U6691E
04
0.30375E-02
0.766E-04
79.
0.76
0. 0246
27102
0.025
0.030
10
173.5
0.16494E
07
27.24
uasTisE
04
0.302 786-02
0.763E-04
84.
0.76
0.0247
26197
0.020
0.030
11
178.6
0.17048E
07
37*20
Oi20681E
04
0.3C427E-02
0.767E-04
89.
0.75
0. 0244
27101
0.025
0.030
12
183.6
0.17603E
07
37.24
0122668E
04
0.29212E-02
0.755 E-04
94.
0.77
0.0251
26199
0.023
0.029
13
187.5
0. 18024E
07
36.46
0i24212E
04
0.29245E-02
0.102E-03
96.
14
190.1
0.1B310E
07
36.42
C125023E
04
0.274 E5E-02
O.lOlE-03
96.
15
192.7
0.18595E
07
36. 60
Ci25795E
04
O.265O4E-02
0.984E-04
96.
16
195.4
0. 16882E
07
36.88
0126539E
04
0.25576E-02
0.940E-04
96.
17
198.0
0.19169E
07
36. 95
Ci27262E
04
0.24965E-02
0.9226-04
96.
18
200.6
0.19454E
07
36.95
01279696
04
0.24527E-02
0.905E-04
96.
19
203.2
0.19740E
07
36.97
0128657E
04
0. 236236-02
0.867 E-04
96.
20
205.8
0.20025E
07
37.07
0129333E
04
0.23613E-02
0.871E-04
96.
21
208.5
0.20311E
07
37. C5
0129997E
04
O.2206OE-O2
0.841 E-04
96.
22
211.1
0.20596E
07
37.16
0130641E
04
0.22222E-02
0.836E-04
96.
23
213.7
0.20682E
07
37.11
0431272E
04
0.218906-02
0.812E-04
96.
24
216.3
0.21169E
07
37.26
0131896E
04
0.21898E-02
0.828E-04
96.
25
218.9
0.2145 6E
07
27.24
0i325l9E
04
0.21542E-02
0.006 E-04
96.
26
221.6
0.21741E
07
37.26
j0i33d32E
04
0.21409E-02
0.B16E-04
96.
27
224.2
0.22027E
07
26.93
Q133763E
04
0.22711E-02
0.825E-04
96.
28
226.8
0.22312E
07
37,39
0134377E
04
0.202266- 02
0.7866-04
96.
29
229.4
0.22598E
07
37.22
0134953E
04
0.20090E-02
0.739E-04
96.
30
232.0
0.22883E
07
27. 58
0135527E
04
0.2C086E-02
0.7 72 E-04
96.
31
234.6
0.23169E
07
37.58
0136095E
04
0.19604E-02
0.744E-04
96.
32
237.3
0.23456E
07
37.49
0136651E
04
0.193186-02
0.734 E-04
96.
33
239.9
0.23 743E
07
37.47
0137202E
04
0.19223E-02
0.736E-04
96.
34
242.5
0.24026E
07
37.24
0137747E
04
0.189326-02
0.705 E-04
96.
35
245.1
0.24314E
07
37.45
0i38285E
04
0. 18710E-02
0. 7406-04
96.
36
247.8
C.245S9E
07
37.22
0138811E
04
0.180616-02
0.7 79 E-04
96.
UNCERTAINTY IN REX=27721. UNCERTAINTY IN F=0. 05034 IN RATIO
RUN 081574-2 *** DISCRETE HCLE PIC ♦** NAS-3-14336
STANTON NUMBER DATA
TAOB=
• 2 7.84
DEG C
UINF
■=
17.14 M/S
TINF= 27.72
DEG C
RHO»
1.162
KG/M3
vase
= 0.15776E-04 M2/S
XVO= 22.4
CM
CP=
1015.
J/KGK
PR =
0*717
***
2700STEP75 H=0.75
w—t
II
X
p/0=5 ***
PLATE
X
REX
TO
REcNTH
STANTCN ^C
OST
OREEN
M
F
T2
THETA
DT^
1
127.8
0.11453E
07
40. 28
0*92 83 8E
02
0.3363-9E-02
0.670E-04
2.
2
132.8
0.120056
07
40.26
0126297E
03
0.28007E-02
0.629E-04
35.
0.71
0.0231
39A98
0.978
0.025
3
137.9
0. 12557E
07
40.28
0U6658E
04
0.2833 8E-02
0.630E-04
61.
0.70
0.0227
39195
0.974
0.025
4
143.0
0.13109E
07
40.28
0i30314E
04
0.25184E-02
0.609E-04
78.
0.70
0.0228
40133
1.004
0.025
5
148.1
0.13661E
07
40. 28
0i44256E
04
0.22538E-02
0. 5936-04
93 .
0.71
0.0230
39197
0.975
0.025
6
15 3.2
0. 14 21 3E
07
40.26
Oi57'862E
04
0-21482 E-02
0.587E-04
105.
O.Tl
0.0230
39178
0.962
0.025
7
158.2
0.14765E
07
40.28
Oi71236E
04
0.20589E-02
0-582 E-04
116.
0.71
0.0229
39175
0.958
0.025
8
163.3
0.15317E
07
40.26
0i84462E
04
0.202 5 5 6- 02
0.581E-04
126.
0-70
0.0227
39198
0.978
0.025
9
168.4
0.15869E
07
40.28
Ci97825E
04
0.19362E-02
0.575E-04
135.
0.69
0.0223
39136
0-927
0-024
10
173.5
0.16421E
07
40.26
<J*11030E
05
0.19066E-02
0.574E-04
142.
0.70
0.0226
36169
0.875
0.024
11
178.6
0.16973E
07
40.20
Oil2222E
05
0.18412E-02
0.569E-04
148.
0.70
0.0226
37167
0.791
0.024
12
183.6
0.17 525E
Q7
40.30
0113308E
05
0.179 5 8E-02
0.567E-04
154.
0.72
0.0233
37121
0.755
0.024
12
187.5
0. 179.44E
07
29.44
0U4352E
05
0. 169888-02
0.603 E-04
157.
14
190.1
0.18228E
07
39.31
0il4399E
05
0.16490E-02
0.628E-04
157.
15
192.7
0.18513E
07
29.64
Oil4446E
05
0.15942E-02
0.618E-04
157.
16
195.4
O.1079OE
07
29.69
0.14490E
05
0.15393E-02
0. 5916-04
157.
17
198.0
C.19CS4E
07
39.75
CU4533E
05
0.150018-02
0.5 80 E-04
157.
18
200.6
0.19368E
07
39.77
0*14575E
05
0.145626- 02
0.568 E-04
157.
IS
203.2
0.19653E
07
39.79
0U4616E
05
0. 14061E-02
0.541E-C4
157.
20
2U5.8
a.l993 7E
07
39-94
0*14656E
05
0.13811E-02
0.5 39 E-04
157.
21
208.5
0 . 20 221E
07
39.92
0.14695E
05
0.13327E-02
0.522E-04
157.
22
211.1
0.20505E
07
39.94
0il4732E
05
0.13151E-02
0. 5256-04
157.
23
213.7
0.20790E
07
39-94
01147696
05
0.12753 E-02
0.5096-04
157.
24
216.3
0. 2107 5E
07
40-C9
01148056
05
0.125548-02
0.5156-04
157.
25
218.9
0.21361E
07
40. C5
01148406
05
0. 12274E-02
0.499E-04
157.
26
221.6
0.21 64 5E
07
40.00
0H4876E
05
0.1 2644 E-02
0.514E-04
157.
27
224.2
0.21929c
07
39.82
0114912E
05
0.127C6E- 02
0.503E-04
157.
28
226.8
0-22214E
07
40.15
0*14947E
05
0. 116548-02
0.493E-04
157.
29
229.4
0.224986
07
40.00
0114980E
05
0.11728E-02
0.467E-04
157.
30
232.0
0.22782E
07
40.28
0115013E
05
0.116816-02
0.492E-04
157.
31
234.6
C.23066E
07
40. 28
0.15046E
05
0.11438E-02
0.476 E-04
157.
32
237.3
0-23 352E
07
40.17
01150786
05
0.11338E-02
0.472E-04
157.
33
239.9
0.23638E
07
40.15
0115111E
05
0.11349E-02
0.473E-04
157.
34
242.5
0.23922E
07
39.98
CU5143E
05
0.11053E-02
0.450 E-04
157.
35
245.1
0.242B6E
07
40.13
0H51T4E
05
0.11046E-02
0.484E-04
157.
36
247.8
0. 24490 E
07
59.92
Cil5205fc
05
O.1C650E-C2
0.5 07 E-04
157.
UNCERTAINTY IN REX=2 75SE.
UNCERTAINTY IN F = (]-05034 IN RATIO
0(7 [
RUN
081574- 1
OISCRcTE
HCLE PIG
**♦ NAS-3-14336
STANTON
NUMBER
DATA
***
2700STCP75 M=0.75
TH=0
P/D«5
FUN
□81574-2
*** DISCRETE
HOLE PI(
*** NAS-3-14336
STANTON
NUMBER
DATA
2700STEP75 M*C. 75
-t
X
II
P/D«E
LINEAR SUPERPDSITICN IS APPLItC TO STANTCN NUMBER CATA FROM
PLN NUMBERS 081574-1 AND C31574-2 7D OBTAIN STANTCN NUMBER DATA AT TH=0 AND TH=1
PLATE
PC XCCL
tF DEL2
ST (Th=0 )
PEXHOT
R E DEL2
ST(TH=U
ETA
STCR
F-COL
STMR
5-HOT
LOGB
1
1150408. 0
99. .7
0.C03598
1145315.0
92. E
C. 003364
ULUUU
1.027
0.0000
0.960
0.0000
0.960
2
1205849. 0
287 .4
0.003173
1200511.0
262.7
0.032792
0.120
0.836
0.0250
1,001
0.0231
3.718
3
1261291. 0
468 • 0
0. 003342
1255707.0
1693.2
0.002B21
0.156
0.9 86
0.0245
1.075
0.0227
3.921
4
1216732. 0
653.2
0.003339
1310903,0
3090. e
0.00250S
Oi248
1.061
0.0250
t.996
0.0226
3,914
5
1372173.0
834.5
0. C02199
1 366099,0
4479.4
0.002243
0.299
1.074
0.0246
0,919
0.0230
3.096
6
1427615.0
1010.3
0. C03143
1421295.0
5070.6
0.002116
0.327
1. 103
0. 0247
0,690
0.0230
3.911
7
1433056. 0
1 184 .2
.1.003132
1476491.0
7254. 3
■ CfOQ2.9H,
0*357
1.140
0.0246
0,666
0.0229
3.914
8
1538497.0
13 55.7
0. C33054
1531687.0
8628.2
!0. 001991 \
0^348
1.147
0.0251
0.673
0.0 227
3.957
9
1593939.0
1525 .5
0.C03071
1586083.0
9990.0
0. 001879
0*388
1.186
0,0246
B.638
0.0223
3.894
10
16492B0. 0
1695 .3
0.003056
1642079.0
11322.0
0.001780
0.418
1.209
0.0247
Q. 806
0.0226
3.907
11
170+822. 0
16 65 .3
0. C03C76
1697275.0
12656. 8
0.482
1.244
0,0244
0.732
0.0 226
3.816
12
1760263. C
2032.5
1 0. C029571
1752471.0
13990. 5
[0.00145^J
0*508
1.219
0.025L
0.677
0.0233
3.826
13
1E02398.0
2156 .9
0. CC2962
1794420. 0
15334. £
0.001327
0.552
1.239
0.624
14
183095 1.0
2239.0
0. C02783
1822846.0
15372.4
0.001315
Oi527
1. 174
0.622
15
1E59503. 0
2217.1
0.002684
1851272.0
15409.2
0.001274
0*525
1.142
0.606
16
1E8B194. 0
2392 .5
0. 002590
1 879835.0
15444.8
0.001230
0*525
1.111
0.588
17
1 916885.0
2465.7
0.C02528
1908399.0
15479.4
C. 001198
0*526
1.094
0.576
18
1945437. 0
2537.3
0, C02484
1 636825.0
15512. 9
0. 001156
0*534
1.083
0.559
19
1973989. 0
2607 .0
0.002393
L965251.0
15545.2
0.001116
0*534
1.051
0. 542
20
2002541. 0
2675.4
0. C02392
1993677.0
15576.5
0.001084
0*547
1.058
0.529
2 i
2031C94.0
2742.7
0.002216
2022103.0
15606.6
0.001043
0*550
1.032
a. 51 2
22
2059646.0
2008 . J
0. 002251
205C529. 0
15636.4
0.001040
0*538
1.009
0.513
23
2C63199. 0
2671 .9
3.002218
2078955.0
15665.4
0. 000998
0*550
1.001
0.494
24
2116889. U
2935.3
0. CC2220
21C7518.0
15693.5
C. 000972
0*562
1.008
0.484
25
2145580. 0
2998 .3
0.002184
2136082.0
15720.8
0.000946
0.567
0.998
0.473
26
2174 132. 0
3060.5
0. 002169
2 164508.0
15748.4
0.000998
0*540
0.997
0.501
27
2202685. 0
3124.4
0. C02303
2192934.0
15776.4
0.000967
0.580
1.065
fi.488
28
2221237. 0
2186.6
0. 002050
2221360.0
15803.0
0.000905
0*558
0.953
0,458
29
2259790.0
3245 ,0
0.C02O36
2249786.0
15826.0
0.000919
0.549
0,952
0.467
30
2288342. 0
2303.2
0.CO2035
2278212.0
15855,1
0.000913
0*551
0.957
0.466
21
2316B94. 0
3360.6
0. C0I986
2306636-0
1588C.e
0.000896
0*549
0.93B
0.459
22
2245585. 0
3417.0
0.001957
2335202.0
15906,3
0. 000892
0.544
0,929
0.458
23
2374276.0
3472.8
3,001947
2363766. 0
15931.7
C. 000896
0.540
0,929
B.462
34
2402828. 0
3528.1
0,0019 18
2392192.0
159 56.8
0.000866
0*548
0,920
6.449
35
2431380.0
3582.6
0. C01895
2420617.0
15981.5
0.000872
0*540
0.913
0.453
36
2459933. 0
3635.6
0.001630
2449043,0
16005.6
0.000840
0.541
0.886
0.438
STANTCN NUMBER RATIO BASEC ON ST >* PR++0 .4= 0 .0Z95*RE X** , 2) ♦( 1.- ( X I/( X-XVOM **0. 9) ** ( -1. /9 . I
y-ANTCN NUMBER RATIO FOR TH=1 IS CCNVERTED TO COMPARABLE TRANSPIRATION VALUE
L5ING ALOGd + B)/B EXPRESSION IN THE BIOWN SECTION
im
RUN 081S74-1 ♦** DISCRETE HOLE RIE NAS-3- 14336 STANTON NUMBER DATA
TADB*
= 25.27
DEG C
UINF
>X
13.14 rt/S
TINF* 25.14
DEG C
RHO^
1.173
KG/M3
Vise
* 0.15580E-04 M2/S
XVC* 22.4
CM
CP*
1011.
J/KGK
PR=*
01715
***
2 700STEP90 H=0-9
TH*C
F/D*5
PLATE X
REX
TO
REENTH
STANTCN NO
DST
DREEN
M
F
T2
THETA
0T4
1
127.8
0.11594E
07
26.33
0U00C6E
03
0.35817E-02
0.762E-04
2.
Z
132.8
0.121S3E
07
36.31
0128926E
03
0.31907E-02
0.730 E-04
24.
0-93
0.0301
25136
0.020
0.026
3
137.9
0.12711E
07
26.33
C*50661E
03
0.33762E-02
0.745 E-04
41.
0.93
0.0301
25156
0.038
0*028
4
143.0
0.13270E
07
36.33
017642 IE
03
0.35661E-02
0.761E-04
52.
0.94
0.0303
25154
0.036
0.028
5
148.1
0.1382 9E
07
36.33
0110231E
04
0.351766-02
0.7576-04
62.
0.93
0.0300
25155
0.036
0.028
6
153.2
0. 143B8E
07
36.34
0112760E
04
0.335056-02
0.741E-04
70.
0.93
0.0302
25153
0.035
0.028
7
158.2
0. 14946E
07
36.34
0115233E
04
0.33942E-02
0.745 E-04
78.
0.94
0.0303
25166
0.047
0.027
8
163.3
0.15505E
07
36.34
01I7906E
04
0.3354 86-02
0.742E-04
84.
0.94
0.0303
25168
0.048
0.027
S
168.4
0. 16064E
07
36.34
0120576E
04
0.32798E-02
0.735E-04
91.
0.93
0.0299
25168
0.048
0.027
10
173.5
0.16623E
07
26.31
0123226E
04
0.3302dE-02
0.740E-04
96.
0.91
0.0295
25163
0.044
0.028
11
178.6
0.17181E
07
36.31
0125787E
04
0.32567E-02
0.7 36 E-04
102.
0.92
0.0298
25167
0.048
0.028
12
133.6
0.17740E
07
26-23
C128373E
04
O.31661E-02
0.727E-04
107.
0.92
0.0298
25162
0.043
0.028
13
187.5
0.18165E
07
35.56
0*30434E
04
0.32087E-02
0,110E-03
109.
14
190.1
0.18453E
07
35.51
C131336E
04
0.30504E-02
0.108E-03
109.
15
192.7
0.18740E
07
25.96
0.32194E
04
0.29115E-02
0.105E-03
109.
U
195.4
0.19029E
07
36. C6
0133019E
04
0.28102E-02
O.lOOE-03
109.
17
193.0
0-19319E
07
•36. 17
0133815E
04
0.27198E-02
0.976E-04
109.
18
200.6
0. 19606E
07
36.17
0134592E
04
0.26757E-02
0.9586-04
109.
19
203.2
0.19&94E
07
36.19
0*35349E
04
0.25753E- 02
0.918E-04
109.
20
205.8
0.20182E
07
36.29
0.36093E
04
0.259266-02
0.9 27 E-04
109-
21
208.5
0.20470E
07
36.31
Q436825E
04
0.24881E-02
0.889E-04
109.
22
211.1
0.20757E
07
36.42
0.37536E
04
0.24452E-02
0.8876-04
109.
23
213.7
0.21045E
07
36.40
0438229E
04
0.23666E-02
0.852E-04
109.
24
216.3
0.21334E
07
36.53
0*38916E
04
0 .24042E-02
0.875E-04
100.
25
213.9
0. 21623E
07
36.53
a.39605E
04
D. 237786-02
0.8596-04
109.
26
221.6
0.21911E
07
36.55
0A40287E
04
0.23543E-02
0.865E-04
110.
27
224.2
0. 22199E
07
36.21
0140985E
04
0.24904E-02
0.8 74 E-04
110.
28
220.8
0.224B7E
07
36.69
■0141665E
04
0.22346E-02
0.835E-04
110.
29
229.4
0.22774E
07
36.50
0142305E
04
0.22083E-02
0.784F-04
no.
30
232.0
0.23062E
07
26.88
0142945E
04
0.22326E-02
0.823E-04
no.
31
234.6
0.23350E
07
36.92
C143579E
04
0.2 17176-02
0.795E-04
no.
32
237.3
0.23639E
07
36.78
Oi44199E
04
0-5 1317E-02
0.778E-04
no.
33
239.9
0.23928c
07
26.74
0144813E
04
0. 212996-02
0.7836-04
no.
34
242.5
0.242l6t
07
36.50
C.45420E
04
0.2C792E-02
0.745E-04
no.
35
245.1
0.24 504 E
07
36.72
0146 01 7E
04
0.20690E-02
0-783 E-C4
no.
36
247-8
0.24791E
07
36.48
01466C4E
04
0.2C042E-02
0.8 24 E-04
no.
UNCERTAINTY IN REX=27937. UNCERTAINTY IN F*0.05033 IN RATIO
FUN 081974-2 0TSCR?T£ HOLE RIG NAS-3- 14336
^tantcm number data
TACe =
26.63
OtG C
UINF
=
n.05 N/S
TINF= 26.51
DEG C
FHO*
1 . 166
KG/M3
V ISC
= 0.15703E-04 M2/S
XVC= 22.4
CM
CP =
1013.
J/KGK
PR =
Ci7l5
41*
2700STEP90 M=0. 9
TH = 1
F/0*5 *♦*
PL ATE
X
REX
TO
reenth
STANTCN NO
DST
DREcN
F
T2
THETA
DTH
1
127.8
0. 114'4 2E
07
40.20
0*921596
02
0.33425E-02
0. 6196-04
2.
2
132-a
0.11 9946
07
40. 19
0i.26l05E
03
0.27830E-02
0.581E-04
43 .
0.85
0.0275
40i52
1.024
0.023
3
137.9
0.12545E
07
40. 19
0-19703E
04
0.295996-02
0.593E-04
74.
0,85
0.0276
40A33
1.011
0.023
. 4
143,0
0.13097E
07
40.19
0136668E
04
0. 28056E-02
0.583E-C4
95,
0.84
0.0273
40L41
1.017
0.023
5
148.1
0.13648E
07
40. 19
01534706
04
0.256686-02
0.567 E-04
113.
0.85
0.0274.
40129
1.007
0.023
6
153-2
0. 14200E
07
40. 20
Cl 70C37E
04
0.23464E-C2
0.553E-04
127.
0.85
0.0276
39185
0.974
0-023
7
158.2
0.1475 IE
07
40.20
0.86169E
04
0.23251E-02
0.552E-04
140.
0.86
0.0279
39170
0.963
0.023
• 8
163-3
0.15303E
07
40.22
OU0223E
05
0.22408E-02
0.546E-04
151 .
0.84
0.0272
39*79
0.969
0-023
S
168.4
0. 15854E
07
40.20
O1II8OOE
05
0.214 77E-02
0.542 E-04
162.
0.85
0.0276
39155
0.953
0.022
10
17 3.5
0.164056
07
40. 19
0113365E
05
0.208886-02
0.540E-04
171.
0.84
0.0271
39119
0.9 27
0.022
11
178.6
0.16957c
07
40. 19
0H4863E
05
0.20024E-02
0.535E-04
180.
0.85
0.0275
38178
0.898
0.022
12
183-6
0.175086
07
40. 19
01163346
05
0.194 90E-02
0.532E-04
188.
0.85
0.0275-
38114
0.851
0.022
13
187-5
0.1792 7E
07
39.43
0il7705E
05
0.18659E-02
0.6476-04
191 .
14
190.1
0.18211E
07
39.21
0.177576
05
0.180 74E-02
0.659E-04
191.
15
192.7
0.18495E
07
39.67
O.178O0E
05
0.17504E-02
0.651E-04
191.
16
195.4
0. 18781E
07
29.75
01178576
05
0.16826E-02
0.620 e-04
191.
17
198.0
0. 1906 6 E
07
39. E2
0H7904E
05
0. 16327E-02
0.6 06 E-04
191.
18
200.6
0. 19350E
07
39. 86
01179496
05
0.15896E-02
0.593E-04
191.
19
203.2
0.19 63 4E
07
39. 80
0117994E
05
0, 152336-02
0. 562E-04
191 .
20
205.8
0. 19918E
07
40. .03
0118837E
05
0.150 24E-02
0.561E-04
191.
21
20 8.5
0.20202E
07
40. 03
Cil8079E
05
0.14493E-02
0.542E-04
191.
22
211.1
0.2 048 6E
07
40.09
0118119E
05
0.14166E-02
0.541E-04
191.
'
23
213.7
0.207706
07
40.07
0118159E
05
O.13730E-O2
0.521E-04
191.
24
216.3
0.2L055E
07
40.22
01181986
05
0.13722E-02
0.532E-04
191.
25
218.9
0.21341E
07
40.22
0-18237E
05
0- 13287E-02
0. 5146- 04
191.
26
221.6
0.21 62 5E
07
<0. 17
01182756
05
0. 135666-02
0.526E-04
191 .
27
224.2
0.21909E
07
39.96
0H8314E
05
0.13822E-02
0.517E-04
191.
28
226.8
0. 22193E
0 7
40.32
011&351E
05
0,126166-02
0.505E-04
191.
29
229.4
0.224776
07
40. 19
0118367E
05
0.12423E-02
0.472E-04
191.
30
232.0
0.22761E
07
40.49
01184226
05
0.12512E-02
0.4996-04
191,
31
234.6
0.230456
07
40.4 9
01184586
05
0.12284E-C2
0.484E-04
191.
32
237-3
0-23330E
07
40.36
0118492E
05
0.12060E-02
0.476F- 04
191.
33
239.9
0.23616E
07
40.36
0118526E
OS
0.11984E-02
0.476 E-04
191 -
34
242.5
0.23900E
07
40-17
011B560E
05
0. 11722E-02
0.453E-04
191.
35
245.1
0.241B4E
07
40.34
0il8593E
05
0.11668E-02
0.483E-04
191 .
36
247-8
0.2446 8E
07
40.13
0118626E
05
0.112136-02
0.5046-04
191.
UNCERTAINTY IN REX»27572.
UNCERTAINTY IN F*C,05034 IN RATIO
143
RUN
081974-1
DISCRETE
HCLE
PIG NAS-3- 143 3 1
STANTON
NUMBER
DATA
**♦ 2700STEP90 M*0.9
TH-0
P/C-5
4**
RUN
081974-2
***
DISCRETE
HOLE
RIt **♦ NAS-3- 14336
STANTON
NUMBER
DATA
2 700STEP90 M*0. 9
7H«l
P/0*5
4t4c
LINEAR SUPERPOSITION IS APPLIED
TO STANTCN NUMBER DATA
FROM
PLN NUMBERS 081974-1 AND C81S74-2 TG OBTAIN STANTCN NUMBER DATA AT TH*0 AND TH«1
PLATE
REXCOL
RE ca2
ST(TH=0 )
REXHOT
RE CEL2
ST<TH*1)
ETA
STCR
F-COL
STHR
= -MOT
L3GB
1
1159394-0
100.1
0.C03582
1144244.0
92-2
C. 003342
uuuuu
1.023
0.0000
•«954
0.0000
0.954
2
1215269.0
289 , 5
0. 003199
1199388.0
261.3
0.002793
0*127
0. 843
0.0301
t.OOO
0.0275
4.125
3
1271142.0
473 .5
0.C03388
1254532.0
1934.2
0.002967
0*124
1.000
0.0301
2.129
0.0276
4.501
4
1327C16. 0
668.6
0.C03595
1309677.0
3614.9
0.002816
0*217
1.143
0.0303
1.117
0.0273
4.571
5
1382892.0
668.3
^0. 0025 5J.
1364821.0
5270.6
0.002578^
0*274
1.194
0.0300
1.055
0.0274
4.570
6
1433766.0
1062.2
i 0.003388 1
1419965.0
6916.3
1 0.0023371
0*310
1.190
0. 0302
C.982
0.0276
4.550
7
1494641.0
1253.0
0.CO3441
1475109.0
E567.9
0.002289
01335
1.253
0.0303
t.983
0.0279
4.643
8
1550515.0
1444.4
0.002412
1530254.0
10228.1
0.002199
0*355
1.283
0.0303
0.963
0.0272
4*599
9
1606390.0
1633.1
■3. C03343
1585396.0
11849.8
0.002099
0.372
1,290
0.0299
0*935
0.0276
4.637
10
1662264.0
1820.4
0.C03365
1640542,0
13483.2
0.002007
0.404
1.332
0.0295
0*908
0.0271
4.5B6
11
1718139.0
2U07 .2
7. 002323,^
1695687,0
15084.9
0.001875
0.436
1.344
0.0298
0.861
0.0275
4.589
12
1774013.0
2190.4
1 C.C03235 1
1750831.0
16702.5
0.001764
01455
1.335
0.0298
0.820
0.0 275
4.555
li
1816476.0
2328.1
0.C03262
1792741.0
1E292.0
0.001662
01494
1.373
e. 780
14
1845253.0
2420.3
0. C03116
1821140.0
18338.6
0.001619
01481
1.316
0.764
15
1674028. 0
2508.0
0,002975
1849539.0
1E3E4.C
0.001574
01471
1.267
0.748
16
1902943.0
2 592.3
C. CC2672
1878076.0
1642 7.9
0.001511
0*474
1.233
8.722
17
1931656.0
2673 ,7
0.002779
1906613.0
18470.3
0.001468
0i472
1.203
0.705
Id .
1960C34.0 .
2753.1
0. CC2735
1935013.0
16511.4
0.001425
01479
1.193
. 0.688
19
1989409.0
2830 .4
0.C0263B
1 963412.0
16551.0
C. 001364
01482
1.157
0.662
20
2018184.0
2906.5
0. C02652
1991811.0
18589,4
0.00133?
0i496
1.174
0.652
21
204o 960.0
2981 .4
0.002545
2020211.0
16626. e
0.001292
0.492
1.134
0*633
22
2C75735.0
2054.1
0.C02501
2043610.0
16663.1
0.001260
01496
1.122
0.621
23
2104511.0
3125.0
0.C02421
2077C09.0
16698,4
0.001222
0i495
1.093
0.605
24
2132425. C
3195,3
0.002460
2105546.0
16733.0
0.001216
0.506
1.118
0.604
25
2162340.0
3265.8
0.C02435
2134084.0
16766.9
0.001169
01520
1.113
0.584
26
2191116.0
3335 .6
0. CO 2409
2162483.0
18600.7
0.001205
0*500
1.108
0.604
27
2219891.0
3407.0
0.002551
2190862.0
18835.1
0.001214
0-524
1.180
0.611
28
2248666.0
3476 .7
0.002283
2219281.0
16368.2
C. 001114
01513
1.064
0.563
29
2277442. 0
3542.3
0.002261
2247681.0
18899.6
C. 001096
01615
1.057
0.556
30
2306217.0
3607.8
0.002286
2276080.0
1693C.8
0.001102
0.518
1.075
0*562
31
2224993. 0
3672.7
0.C02223
23044 80.0
18961.9
0.001085
0.512
1.051
0*555
22
2363907.0
3736 .2
0.C02182
2333017.0
18992.5
C. 001065
Oi512
1.037
0*547
23
2392822. 0
3799.0
0.002181
2361554.0
19022.7
0.031057
0*515
1.041
0.545
34
2421596. 0
3861 .1
0.002129
2389953.0
19052.4
C. 001036
0.513
1.021
0.536
25
2450373,0
3922.3
0.C02118
2418352,0
19081.8
0,001030
0*514
1.021
0.535
36
2479148.0
3982.3
0.002052
2446752.0
19110.5
0.000987
0*519
0.994
0.514
STftNTCN NUMBER RATIO BASED ON ST*PR** 0. 4=0. 029 5*REX** (-.2 I * U { Xl / (X-XVO » »**0 .9 -1 -/9. I
STANTCN NUMBER RATIO FOR TH=1 IS CCNVERTED TO COMPARABLE TRANSPIRATION VALUE
USING ALOGd + 8)/B EXPRESSION IN THE BLQ^N SECTION
RUN 09237A DISCRETE HCL6 RI6*»* NAS-3-14336
STANTCN NUMBER DATA
TAOB*
23.77
DEG C
UINF
' 3
13.47 M/S
TINF= 23.63
DEG C
RHOf:
1.170
KG/M3
Vise
= 0.15526E-04 M2/S
XVC= 22.4
CM
CP«
1014.
J/KGK
PR =
01717
***
2700STEP130
=1 .3
0
II
1
P/D=5
PLATE
X
REX
TO
SEENTH
STANTCN NO
OST
DREEN
M
F
T2
THETA
DTM
1
127.8
0.11853E
07
34.21
0.10173E
03
0. 35604E- 02
0.7916-04
2.
i
132.8
0.12429E
07
34. 21
0i29203E
03
0.30997E-02
0.7516-04
36.
1,33
0.0432
23498
0.033
0.029
3
137-9
0. 1309IE
07
'34.25
C.55365E
03
0.32452E-02
0. 7606-04
63.
1.33
0.0431
24400
0.035
0.029
4
143.0
0. 13572E
07
34. 23
C184341E
03
0.38753E-02
0.819E-04
80.
1.32
0.0426
24106
0.041
0.029
5
148.1
0. 14144E
01
34.23
0U1666E
04
0.396446-02
0.828E-04
95.
1. 34
0.0433
24110
0.044
0.029
6
153.2
0.14715E
07
34, 23
0415CC7E
04
0.389686-02
0.8216-04
108 .
1.33
0.0429
24il6
0.050
0.029
7
158.2
0.15286E
07
34.21
0ad399E
04
0.36900E-02
0.803 6-04
119.
1.32
0.042 8
24137
0.070
0.029
8
163.3
0.15858E
07
24.21
0122182E
04
0.359156-02
0.7946-04
129.
1.32
0.0426
24141
0.073
0.029
9
168.4
0.16429E
07
34.21
0126014E
04
0.35789E-02
0.7936-04
139.
1.33
0.0430
24143
0.075
0.029
10
173.5
0. 170QIE
07
24. 23
Q*29903E
04
0.358986-02
0.7926-04
148.
1.32
0.0427
24137
0.070
0. 029
11
178.6
0. 17 5726
07
34.23
0133667E
04
0.360476-02
0.7946-04
156.
1.30
0.0419
24447
0.079
0.029
12
183.6
0. 18144E
07
24.21
Ci37598E
04
0.350316-02
0.7866-04
164.
1.30
0.0421
24146
0.078
0.029
13
187.5
0.18579E
07
33.20
0140999E
04
0.35767E-02
0. 1226-03
168.
14
190.1
0. 18872E
07
33. C8
0142O34E
04
0. 344546-02
0.123E-03
168.
15
192.7
0.19167E
07
23. 50
C143027E
04
0.32992E-02
0.119E-03
168.
16
195.4
0.19462E
07
33.56
0*43982E
04
0.31810E-02
0.1146-03
168.
17
198.0
0.19753E
07
33.62
C144911E
04
0. 212676-02
0.112E-03
168 .
18
200.6
0.20052E
07
33.65
0145823E
04
0.3 06 3 9 £-02
0.1106-03
168.
19
203.2
0.20347E
07
33.69
0*467C9E
04
0.2946 8E-02
0.1056-03
168.
20
205,8
0.20641E
07
33. 81
0^47 5 78E
04
0.295C7E-02
0.106 6-03
168-
21
208.5
J. 2(J935E
07
33.75
C148433E
04
0.26576E-02
0.102 E-03
168 .
22
21L.1
0.212305
07
33. £5
0149 27 2E
04
0.283576-02
0.1036-03
168.
23
213. 7
0. 21524E
07
33. 79
0150099E
04
0. 277356-02
0.9936-04
168.
24
216.3
0. 218205
07
33.96
01509166
04
0 .277576-02
0.1016-03
168.
25
218.9
3. 221155
07
33. 90
0151 7316
04
0.275556-02
0.9946-04
168.
26
221.6
0.224105
07
33. 85
01525356
04
0.2703 8E-02
0. L02C-03
168.
27
224.2
0.227045
07
32.72
0153321E
04
0.262996-02
0.9046-04
168.
28
226.8
0.229985
07
33. 88
C 154101E
04
0.266C6E-02
0. 101E-C3
168.
29
229.4
0.23293E
07
23.85
0*54874E
04
0 .258596-02
0.9226-04
168-
30
232 .U
3.23587E
07
34.23
C155642E
04
0.262726-02
0.963fc-04
168.
31
234.6
0.23881E
07
34.25
0*56405E
04
0 .25566E-02
0.9296-04
168.
3 2
237. 3
0. 24177E
07
24.13
0157148E
04
0.24850E-02
0.9026-04
166.
33
239.9
0.24473E
07
24. 13
0157880E
04
0 .2^8126-02
0.9096-04
168.
34
242-5
0.24767E
07
23. 68
C158604E
04
0.243596-02
0.871E-04
163.
35
245.1
0,2506ie
07
34. 11
0159321E
04
0.242 7 8E-02
0.9076-04
168.
36
247.8
0. 25 356E
07
33. 94
Q160024E
04
0 -23481E-02
0.9456-04
168,
UNCERTAINTY IN REX=2fi572. UNCERTAINTY IN F=0. 05021 IN RATIO
RUN C92474 *** DISCRETE HOLE RIG *♦* NAS-3-14336
STANTCN NUMBER DATA
TACE
= 21.61
DEG C
UiNFs
li.39 M/S
TINF= 21.47
DEG C
RHO*
1.183
KG/ M3
V.ISC* 0.15278E-04 M2/S
XVC= 22.4
CM
CP»
1013.
J/KGK
PR=
01717
***
2700STEP130 M=
a. 3
TH=1
P/C=5 ♦**
PLATE X
REX
TO
REENTH
STANTCN NO
OST
DREEN
M
F
T2
THEI A
1
127.8
0. 120D0E
07
37.90
0110022E
03
0.34660E-02
0.522E-04
2.
2
132.8
0.12 57 86
07
37.90
01279C7E
03
0.271946-02
0.474E-04
5 8.
1.19
0.0386
37i07
0.949
3
137.9
0.13156E
07
37.92
0-25665E
04
0.30319E-02
0.493 E- 04
100.
1.21
0. 0391
37i28
0.9 61
4
143.0
0.137356
07
37.92
01491966
04
0.324 HE- 02
0.506E-04
131.
1.22
0.0394
37i78
0.991
5
148.1
0.14313E
07
37.92
0.73609E
04
0.310 25E-02
0.497E-04
156.
1.22
0.0394
36*26
1.021
6
153.2
0. 14891E
07
37.92
01985616
04
0.27723E-02
0.477 E-04
181.
1.21
0.0391
38il5
1.014
7
158.2
0. 15470 E
07
37.92
0^123056
05
0.27106E-02
0.473E-04
201.
1.19
0.0385
38.33
1.025
8
163.3
0. 16 0486
07
37-90
0114740E
05
0.25496E-02
0.464E-04
219.
1.18
0.0362
38i59
1.042
9
168.4
0.16626E
07
37.92
Q117166E
05
0.241 0 7E-O2
0.457E-04
236.
1.18
0.0384
38i57
1.039
10
173.5
0.17204E
07
37.92
0119629E
05
0.23468E-02
0.453E-04
251.
1.20
0.0389
38*31
1.024
11
178.6
0.177B3E
07
37.92
01220646
05
0.223 606-02
0.447 E-04
266.
1.18
0.0382
38^25
1.020
12
18 3.6
0.18361E
07
37.92
0124443E
05
0.21346E-02
O.442E-04
279.
1.19
0.0365
37.61
0.981
13
187.5
0. 18801 E
07
36.44
0*26 7 14E
05
0. 178466-02
0.581E-04
2 85.
14
190.1
0.19Q98E
07
36. 17
0126767E
05
0.17727E-02
0.616E-04
2 85.
15
192.7
0.19 39. 6E
07
36.55
0.26819E
05
0.171156-02
0.613E-04
285.
16
195.4
0. 19695E
07
36.61
C 126 8696
05
0.16526E-02
0.586 E-04
285.
17
198.0
0.19995E
07
36.67
0126918E
05
0.16149E-02
0.574E-04
2 85.
IB
200.6
0.2029 3E
07
36. 14
012696 5E
05
0.15532E-02
0.557E-04
285.
19
203.2
0.20590E
07
36.60
0127C116
05
0. 148636-02
0.530E-04
285.
20
205.8
0.20888E
07
36. S3
0127055E
05
0.148296-02
0.531E-04
2 85.
21
208.5
0.211B6E
07
36. 97
C127C98E
05
0.14077E-02
0.506E-04
285.
22
211.1
0.214B4E
07
37.05
0127140E
05
0. 139476-02
0.510E-04
285.
23
213.7
0.21782E
07
n»C3
0127181E
05
0.134136-02
0.488E-04
285.
24
216.3
G.22081E
07
27.24
0127221E
05
0.133816-02
0.499E-04
285.
25
218.9
0.223^0E
07
37. 18
0127260E
05
0. 131986-02
0.485E-04
285.
26
221.6
0.22678E
07
37. 12
0127299E
05
0. 128976-02
0.498E-04
2 85.
27
224.2
0.22976E
07
36.27
0127336E
05
O.11550E-O2
0.406E-04
285.
28
226.8
0.23274E
07
37.20
0127312E
05
0.125966-02
0.492E-04
265.
29
229.4
0.235726
07
37.16
01274096
05
0.122566-02
0.446 E-04
285.
30
232.0
0.23869E
07
37.49
0127446E
05
0. 12591E-02
0.4 75 e-04
285.
31
234.6
0.24 1/6 7E
07
37.52
0127483E
05
0.12124E-02
0.455 E-04
285.
32
237.3
0. 24466E
07
37.39
01275186
05
0. 119386-02
0.446E-04
285.
33
239.9
0.24766E
07
37.39
C127554E
05
0.11854E-02
0.447E-04
285.
34
242.5
0.25064E
07
37.20
0127589E
05
0.11453E-02
0.422E-04
285.
35
245.1
0. 2536 IE
07
37.35
0127 623E
05
0.116 UE-02
0.45 2 E-04
285.
36
247.8
0.25659E
07
37.16
0127657E
05
0.11160E-02
0.471E-04
285.
orn
0.019
0.019
0.019
0.019
0.019
0,019
0.019
0.019
0.019
0.019
0.019
UNCERTAINTY IN REX=2891
UNCERTAINTY IN F«0-05031 IN RATIO
9f7T
RUN
092374
***
DISCRETE HOLE
RIG •** NAS-3-14336
STANTCN
NUMBER
DATA
. ♦** 2700STEP130 M»l,3
TH*0, P/D»5
RUN
092474
***
DISCRETE HOLE
RIG NAS-3- 14 336
STANTCN
NUMBER
DATA
27C0STEP13O M»l,3
TH*l P/D=5
LINEAR SUPBPOSITION IS APPLIED
RUN NUMBERS 09237A AND 092A74
TO STANTON NUMBER CAT A FRCM
TO OBTAIN STANTON NUMBER DATA AT TH*0 AND
TH = 1
PLATE
REXCOL
RE 0EL2
ST (TH*0»
REXHOT
RE DEL 2
STCTH*li
ETA
STCR
F-COL
STHR
F-HOT
LOGS
1
1185771.0
101.7
0.C03560
1199974.0
100.2
0.003466
UUUUU
1.016
0.0000
0.989
0.3000
0.969
2
1242917.0
292.4
0.003113
1257804.0
278.5
0,002698
01133
3.825
0.0432
0,976
0.03 66
5.121
3
1300062.0
474.3
0.003253
1315634.0
2678.9
0.003028
0*069
0.965
0.0431
1,164
0.0391
5.707
4
1357208.0
678.7
0.C03SC1
1373464.0
511,9.9
C. 003226
0.173
1.247
0.0426
1.292
0. 0394
6.114
5
1414354.0
904.5
0.004002
1431295.0
7588.7
0.00 310 8
0*224
1.352
0. 0433
1.285
0. 0394
6.230
6
1471499,0
1131.8
0. C03951
1489125,0
10029.8
3 i293
1,395
0.0429
1.185
0.0 391
6.126
7
1528645.0
1351 .9
0.003751
1546955.0
12449.0
C. 002730
0.272
1.374
0.0428
1.185
0.0385
6.156
6
1585791.0
1563.9
0.00 3669
1604785-0
14829.5
0.002586
0^295
1.387
0. 0426
1.144
0.0382
6.132
9
1642936.0
1 773.5
O.C03668
1662615.0
17186.6
0.002467
0*327
1.425
0.0430
1.111
0.03B4
6.153
10
1700C82.0
1983.6
0.003684
1720445.0
19544.9
0.002387
0.352
1.466
0.0427
1.092
0.0389
6.240
11
1757227.0
2194.9
0.002713
1778275.0
21928.6
0. 002267
0*389
1.510
0.0419
1.052
0.0382
6.14T
12
1814373.0
2404.4
0.003620
1836105.0
24264.5
0.002135
01410
1.502
0.0421
1.003
0.0385
6.140
13
1857804.0
2562.8
0.002729
1 880056.0
2657 E.E
0,001785
0.521
1.569
S.847
14
IE87234.0
2670.6
0.003568
1909839.0
26631. e
0.001773
0.506
1.523
0.846
15
1916664.0
2774.0
0.C03435
1939621.0
26683.8
3.001712
01532
1.470
3.822
16
194623 6.0
2873.4
0.003311
1969548.0
26734. 0
0.001653
01501
1.430
0.796
17
197580S.0
2970.2
0.. 003256
1999475.0
26702.7
0.031615
3.504
1.417
0.784
18
2005239.0
3065 .2
0.003193
2029258.0
26829.9
0.001554
0*513
1.400
0.758
19
2034669.0
3157.5
0.002071
2059040.0
268 75. 3
0.001487
0.316
1.357
0.729
20
2064099.0
3248.0
0.003076
2088822.0
26919.6
0.001483
Ol5l8
1.36B
0.731
21
2093530.0
3337.3
0. C02981
2118605,0
26962.7
C, 001408
0.528
1,336
0.698
22
2122960.0
3424.8
0.C02959
2148388,0
27004.5
0,001395
0*528
1.334
0.694
23
2152390.0
3511.0
0. C02895
2178170.0
27045,4
0.001348
0*534
1.314
0.674
24
2161962.0
3596.4
0.002898
220G097.0
27085.4
C. 001339
0*538
1, 324
0.672
25
2211535.0
3681.4
0. 002878
2238024.0
27125.1
3.001320
0*541
1.323
0.666
26
2240965.0
3765 .5
0.002824
2267807.0
27164. C
0,001290
0.543
1.3 06
0.654
27
2270395.0
3847.7
0.002756
Z297589.0
2720fl.4
0.001156
01580
1. 262
0.588
28
2299825.0
3929.2
O.C02780
2227372.0
27236. 5
0.001260
0.547
1,300
0.644
29
2329255. C
4010.0
0.002702
2357155.0
27273.5
0.001226
0 .546
1.271
0.629
30
2358685.0
4090.2
0.C02744
2386937.0
27310.6
Ic. 001260 1
0.541
1.297
0.649
31
2388115.0
4170.0
0.002671
2416719.0
27347.5
0.001213'
0.546
1.269
0.627
32
2417688.0
4247.6
0.002595
2446646.0
27383.3
0.001194
0.540
1.240
0.620
33
2447261.0
4324.0
0.CO2592
2476573.0
2741 8. E
0.001186
0*5.42
1.244
0.618
34
2476691.0
4399.7
0.002546
2506356.0
27453.6
C. 001146
0.550
1.228
0.599
35
2506121.0
4474.6
0.00 25 36
2536138.0
2 74 8 8. C
0,001162
0.542
1 .229
0.609
36
2535551.0
4548.1
0.002453
2565921.0
27521.9
G. 001116
0.545
1. 195
0.588
STAhTCN ^UMBER RATIO BASEC ON ST>*PR**0*4» 0 ,0295*REX*+ . 2)*( 1 .- ( XI /( X-XVO J ) **0.9 ) «*< (-1. /9. I
STANTCN NUMBER RATIO FOR TH» I IS CCNVERTEP TO COMPARABLE TRANSPIRATION VALUE
USING ALOGd ♦ Bl/B EXPRESSION IN THE BLOWN SECTION
RUN 121174 VELOCnv PPCFILE
REX =
0.12950E 07
REM
2871.
XVO =
13.04 CP.
0EL2
-
0.254
UINF *
16.82 P/S
DEt99=
2.100
VTSC -
0.149026-04 P2/S OELl
-
0.355
PORT =
19
H
~
1.396
XLOC =
127.76 CP.
CF/2
= 0. 164966-02
YICM.)
Y/DEL
U(M/S) U/UINF
y *
U+
0.025
0.012
7.26
0.432
11.6
10.63
0.028
0.013
7.39
0.440
12.8
10.82
0.030
0.015
7.63
0.454
14.0
11.17
0.033
0.016
7.84
0.466
15.1
11.46
0.038
O.OIB
8.22
0.489
17.5
12.03
0.046
0.022
8.56
0.509
21.0
12.53
0.056
0.027
8.99
0.534
25. t)
13.15
0. 069
0.033
9.38
C.558
31.4
13.73
0.084
0.040
9.72
0.578
38.4
14,23
0. 102
0.048
10.00
0.594
46 . 6
14.63
0.122
0.058
10.25
0.609
55.9
15.00
0.147
0.070
10.49
C.624
67.6
15.36
0.178
0.085
10.76
C.640
81 .5
15.75
0.213
0.102
11.06
0.658
97 .6
16.19
0.254
0.121
11.32
0.673
116.4
16.5b
0.300
0.143
11.59
C.689
137.4
16.97
0.351
0.167
11.88
0.706
160.7
17.36
0.414
0.197
12. 18
0.724
189.8
17.83
0.490
0.233
12.51
0.743
224. 7
18.30
0, 592
0,282
12.93
0.768
271.3
18.92
0.719
0.342
13.42
G.798
329.6
19.64
0.871
0.415
13.94
0.826
399 .4
20.40
1.024
0.487
14.43
0.858
469.3
21. 1^
1.214
0,578
14,97
0.890
55o .6
21.91
1.405
0.669
15.46
0.919
644.0
22.63
1.595
0.759
15.89
0.945
731,3
23 * 2o
1.786
0.850
16.25
0.966
818.6
23.79
1.976
0.941
16.56
0.984
906.0
24.24
2. 167
1.032
16.69
0.992
993 .3
24.43
2.357
1.122
16.79
0.998 1080.6
24,58
2.548
1.213
16.82
UOOO 1168.0
24.62
PUN
121174
*** DISCRETE HOLE
RIG *** NAS” 3-14336
STANTON NUMBER DATA
TACB=
19.46
□ EG C
UINF
16.88 P/S
TINF= 19.33
DEG C
PHO=
1. 208
KG/M3
V ISC
= 0.14903E-04 M2/S
XVO= 13.0
CM
CP=
1 011-
J/KGK
PR =
0.716
2900ST
■ EP FP P /D =1 0
+ + ♦
PLATE
X
FEX
TC
PEENTH
STAMEN NO
DST
DREEN
ST(THEO)
RATIO
1
127. 8
0.12997E
07
32.26
0;i0283E
03
0.357 376-02
0.661E-04
2.
3.31195E-02
1.146
2
132.8
0.13572E
07
32.24
0.28901E
03
0.28970E-02
0.611E-04
3 .
0.27498E-02
1.054
3
137.9
0. 14148F
07
3 2.24
0444 890E
03
0 .26599E-02
0.5 94 E-04
4.
0.25879E-02
1.028
<t
143.0
0.14723E
07
32. 26
0i59929E
03
0.256685-02
0.5B7E-04
5.
0. 24836 E-02
1.034
5
148.1
0.15299E
07
32.28
0.74425E
03
0.2^71lE-02
0.580E-04
5.
0.24065E-02
1.027
6
153.2
j. 15 87 4E
0 7
32» 24
C.88572E
03
0.24455E-02
0.580E-04
6.
0.23453E-02
1.043
7
158.2
0.16450E
07
22.28
0.10234E
04
0.23386E-02
0.572E-04
6.
0.22944E-02
1.019
8
163.3
0. 17025E
07
22.24
0ill575E
04
0.23211E-02
0.573E-04
7.
0.22510E-02
1.031
9
168.4
0. 17601E
07
32,22
0.12894E
04
0. 22631E-02
Q.570E-G4
7.
0.22 129 E-02
1.023
10
173.5
G.18176E
07
32. 22
0il4191E
04
0.22473F-02
0.569E-04
8.
0.21792E-02
1.031
11
178.6
0. 18752E
07
32. 24
C*15455E
04
0.21458E-02
0.562E-04
8.
0.21488E-02
0.999
12
183.6
0.19327E
07
32.26
0il6686E
04
0 c21316E-02
0.561E-C4
B.
0-21212E-02
1.005
13
187.5
0. 19765E
07
31. E6
0417617E
04
0.21400E-02
0.739E-04
9.
0.21017 E-02
1.018
14
190.1
0. 20061E
07
31.70
0.18249E
04
0.21224E-02
0.745E-04
9.
0.20892E-02
1.016
15
192.7
0.20357E
07
32. C7
on 8877E
04
0.21089E-02
0.7556-04
9.
0.20772E-02
1.015
16
195.4
0.20 65 5E
07
32.09
0*19501E
04
0.2C966E-02
0.740E-04
9.
0.20656E-02
1.015
17
198.0
0. 20953E
07
32.11
C*20121E
04
0.20855E-02
0.7406-04
9.
0.20544E-02
1.015
18
200.6
0.21249E
07
22.03
0i2O739E
04
0. 20747E-02
0.735E-04
9.
0.204376-02
1.015
19
203.2
0.21546E
07
31.95
0i21353E
04
0.20647E-02
0.7226-04
9.
0.20333E-02
1.015
20
205.8
0,21842E
07
32. C7
Ci21964E
04
0.2C53SE-02
0.727E-04
10.
0,202 33 E-02
1.015
21
208.5
0.22138E
07
22.01
0-22572E
04
0.20447E-02
0.7206-04
10.
0-20136E-02
1.015
22
211.1
0.22435E
07
32.03
Ci231776
04
0.20346E-02
0.728 E-04
10.
0.20042 E-02
1.015
23
213.7
0.22731E
07
31.90
Qi23780E
04
0 .20261E-02
0.716E-04
10.
0.19951E-02
1.016
2^
216.3
C.23C29E
07
31.97
Oi24373E
04
0.19725E-C2
0.707E-04
10.
0.19862E-02
0.993
25
218.9
0.23327E
07
32.07
0i24963E
04
0.2C072E-02
0.721E-04
10.
0.19775E-02
1.015
26
221.6
0. 23e.23E
0 7
31.97
Oi25558E
04
0.19993E-02
0.751E-04
10.
0.19692E-02
1.015
27
224.2
0.23919E
07
30.79
0*26151E
04
0- 19966E-02
0.662E-04
10.
0.19610E-02
1.018
28
226. 8
0.24216E
07
31.99
0-26741E
04
0.19833E-02
J.751E-04
10.
0.19531E-02
1.015
29
229.4
0.24512E
07
31. 91
0427328E
04
0.19755E-C2
0.688E-04
11.
0.19454E-02
1.015
30
232.0
0.248G9E
07
32.39
0*27913E
04
0. 19660E-02
0.7186-04
11.
0.19378E-02
1.015
31
234.6
0.25105E
07
32. 35
0i28495E
04
O.19501E-O2
0.701E-04
11.
0.19305 E-02
1.014
32
237.3
0.254O3E
07
32.20
0i29075E
04
0.19518F-02
0.696E-04
11.
0.19233E-02
1.015
32
239.9
0.25701E
07
22. 18
0i29653E
04
0.19449E- 02
0.702E-04
11.
0.19163E-02
1.015
34
242.5
0.25997E
07
31.88
0*30230E
04
0.19389E-02
0.675E-04
11.
0.19094E-02
1.015
35
245.1
0.26293E
07
32.14
0i30804E
04
0.19311E-02
0.7 15 E-04
11.
0.19027E-02
1.015
36
247.8
0.26590E
07
21.86
0i31376E
04
O.19250E-O2
0.770E-04
11.
0.18962E-02
1.016
RUN 121474 *** DISCRETE HCLE RIG *** NAS-3-14336 STANTCN NUMBER DATA
TAD8=
! 19.34
DEG C
U INF
=
16.71 M/S
TINF= 19,22
DEG C
PHO =
1.215
KG/M3
Vise
= 0.14814E-04 K2/S
XVC= 13.0
CM
CP =
1011.
J/KGK
PR=
0.716
**t
2900STEP40 M=(
3.4
1H=0
P/D?10 ♦**
PLATE
X
REX
TO
REE NTH
STA^TCN NO
CST
OPEEN
M
F
T2
THETA
DTH
1
^^7.8
0. 12945E
07
30.50
0J10312E
03
0.3 59 6 25-02
0.754F-04
2.
2
132.8
0.13 51 8E
07
30. 52
0128954E
03
0.29068E-02
0.695F-04
5,
0.39
0.0032
21.08
0.165
0.027
3
137.9
0.1409IE
07
30.48
0i48118E
03
0. 273125-02
0.684C-04
6.
0.00
0.0032
30148
0.165
0.028
4
143.0
0.14664E
07
20. 50
0i66l96E
03
0.25277E-02
0 .668E-04
8.
0. 39
0.0031
21.36
0.190
0.027
5
148.1
0-15237E
07
30. 52
Ci84019E
03
0.25057E-02
0.666F-04
9.
0.00
0.0031
30152
0,190
0.027
6
153.2
0.15811E
07
30-50
Oil0138E
04
0.23663E-02
0.657E-04
10.
0.39
0.0032
21134
0.188
0.027
7
158.2
0.16384E
07
20. 54
Cill840E
04
0.23745E-02
0.656E-C4
11.
0.00
0.0032
30*54
0.138
0.027
8
163.3
0.16957E
07
30.48
C.13520E
04
0.228796-02
0.653E-C4
12.
0.39
0.0031
21.41
0.194
0.027
«;
168.4
0.17530E
07
30.50
0il5l74E
04
0.22646E-02
0.650E-04
13.
0.00
0.0031
30.50
0.194
0.028
10
173.5
0.18103E
07
30.44
0il6804£
04
0 .22033E-C2
0.650E-04
14.
0.39
0.0032
2U40
0.194
0.027
11
178.6
0.18676E
07
20. 50
0..1B416E
04
0.21898E-02
0.646E-04
14.
0.00
0-0032
30150
0.194
0.028
12
183.6
0.19249E
07
30.48
0A20003E
04
0.21117E-02
0. 642E-04
15.
0.41
0.0033
21.42
0,196
0.027
13
187.5
0.196S5E
07
30.56
Oi21299E
04
0.21801E-02
0. 7826-04
16.
14
190.1
0.199'80E
07
30.48
0i22310E
04
0.21610E-02
0.777E-04
16.
15
192.7
0.20275E
07
30.80
0i22947E
04
0.21497E-02
0.782E-04
16.
16
195.4
0.20572E
07
20. 8C
0423579E
04
0.212 72E-02
0.763E-04
16.
17
198.0
0.20B69E
07
30.62
0.24207E
04
O.212O0E-O2
0.763E-C4
16.
18
200.6
0.21164E
07
30. 79
0124829E
04
0.2C937E-02
0.754E-04
16.
19
203.2
0.21459E
07
30.77
0a25443E
04
0.2C631E-02
0.737E-04
16.
20
205.8
0.21754E
07
23. 64
C..26057E
04
0.208 70E-02
0.750 E-04
16.
21
208.5
C.22049E
07
30.77
C A26669E
04
0.20546E-02
0.734E-04
16.
22
211.1
0.22345E
07
30. E4
Oi27273E
04
0.203 77E-02
0.744E-04
16.
23
213.7
0.22 64CE
07
30.75
CJ27E69E
04
0.19918E-02
0.727E-04
16.
24
216.3
0.22936E
07
-20.61
0.284585
04
0. 19993E-02
0.724E-04
16.
25
213.9
0.23233E
07
20.73
0.29054E
04
0.20324E-02
0.744E-04
17.
26
221.6
0.23S28E
07
30.69
0i29654E
04
0.20281E-02
0.776E-04
17.
27
224.2
0.23823E
07
29.62
0130252E
04
0.2C191E-02
0.690E-04
17.
28
226.8
0. 24118E
0 7
3C.71
0430850E
04
0.2023SE- 02
0,7786-04
17.
29
229.4
0.24414E
07
20.63
0i3l448E
04
0.20237E-02
0.719E- 04
17.
30
232.0
0.24709E
07
21.02
0J32047E
04
0.2C300E-02
0.750E-04
17.
31
234.6
0-25004E
07
= 1,02
0.32642E
04
0.19949E-02
0.728E-04
17.
32
237.3
0.25301E
07
20. 68
0433227E
04
0.19655E-02
0-71 8 E-04
17.
33
239.9
0.25 59 7E
07
30. 80
0.33811E
04
0.1989eE-02
0.728 E-04
17.
34
242.5
0- 25892E
07
20.57
0-34396E-
04
0.19691E-02
0.703E-04
17,
35
245.1
0.26168E
07
20.79
0.34976E
04
0.19543E-02
0.737E-04
17,
36
247.8
0.26483E
07
20. 54
0i35548E
04
0.19203E-02
0.785F-04
17.
UNCERTAINTY IN P.EX=28658,
UNCERTAINTY IN F=0. 05034 IN RATIO
RUN 121274-2 DISCRETE HOLE RI6 **’* NAS-3-14336
STANTCN NUMBER DATA
TACa«
19,92
DEG C
UINF
X
1€.77 M/S
TINF= 15-80
DEG C
RHO*
1.20 6
KG/M3
V ISC
= 0. 14946 E-04 P2/S
XVG= 13.0
CM
CP =
1011.
J/KGK
PR =
0i715
***
2900STEP40 M-0.4
TH=1
P/0*10
PLATE
X
REX
TO
RE6NTF
STANTCN NO
DST
DREEN
M
F
T2
THETA
DT4
1
127.8
0.1287 6E
07
32.47
01985 12E
02
0.3455 8E-02
0.668E-04
2.
2
132.8
0.13446E
07
32.45
0i27435E
03
0.27126E-02
0.613E-04
5.
0. 35
0.0028
31 *86
0.953
0.024
3
137.9
0. 14017E
07
32.47
Q157405E
03
0.24306E-02
0.594E-04
9 .
0.00
0.0026
32*47
0.953
0.025
4
143.0
0.14587E
07
32.45
Ci86.107E
03
0.22676E-02
0.584E-04
11 .
0.35
0.0029
31131
0.910
0.024
C
148.1
0. 15157E
07
32-45
G111340E
04
0-21162E-02
0.576E-04
13.
0.00
0.0029
32*45
0.910
0.025
6
153.2
0.15727E
07
32.43
0kl4005E
04
0.20436E-02
0.572E-04
14.
0.39
0.0031
31154
0.929
0.024
7
158.2
0.16297E
07
32.45
0116819E
04
0.1995QE-02
0.569F,-04
16.
0.00
0.0031
32145
0.929
0.025
8
163.3
0.16 86 7E
07
32-43
0il9605E
04
0.19446E-02
O.567E-04
17.
0.33
0.0027
31167
0.939
0.024
9
168-4
0.1743 7E
07
32.45
C122115E
04
0.18419E-02
0.561E-04
18.
0.00
0.0027
32*45
0.9 39
0.025
10
173.5
0.18007E
07
22.45
Ca24592E
04
0.16267E-02
0.560E-04
20.
0.39
0.0031
31139
0.916
0.024
11
178.6
0.185776
07
32.43
0.27256E
04
0.17890E-02
0.559E-04
21.
0. 00
0.0031
32.43
0.916
0.025
12
183.6
0. 19148E
07
32.43
01298975
04
0.17434E-02
0.557E-04
22.
0.36
0.0029
3U16
0.899
0.024
13
187.5
0. 19581E
07
32.34
0*32 164E
04
0.17712E-02
0.639E-04
22.
lA
190.1
0. 19 87 5 E
07
32. 16
0*34200E
04
0.1B056E-02
0.653E-04
22.
15
192.7
0.20168E
07
32.43
0134735E
04
0.183C7E-02
0.669E-04
22-
16
155.4
0.20463E
07
22.43
0135272E
04
0.18286E-02
0.660E-04
22.
17
198.0
0-20758E
07
32.45
C135811C
04
0.18336E-02
0.664E-04
22.
18
200.6
0.21052E
07
32.29
0136350E
04
0.16335e-02
0. 664E— 04
23.
19
203.2
0-21345E
07
32.22
0*36887E
04
0.1 £24 EE-02
0.652E-04
23.
20
205.8
0.21639E
07
32.39
0137427E
04
0.184766-02
0.665E-04
23.
21
20 8.5
0. 21933E
07
2 2. 34
0137967E
04
0.1E225E-02
0.654 E-04
23.
22
211.1
0-22226E
07
22.37
01385026
04
0, 1E227E-02
0.666E-04
23.
23
213.7
0.22520E
07
32. 26
0139036E
04
0.18065E-02
0.655E-04
23.
24
216.3
0-2281 5E
07
32.24
0*3956 3E
04
0.17813E-02
0.652E-04
23.
25
218.9
0.23110E
07
32.28
C 14009 7E
04
0.184845-02
0.672E-04
23.
26
221.6
0.23404E
07
32. 28
0140637E
04
0.18284E-02
0.698E-04
23.
27
224.2
0.23697E
07
21.28
0141168E
04
0.17867E-02
0.612E-04
23.
28
226.8
0.23991E
07
32.26
0141700E
04
0.1E30 6E-02
0.701E-04
23.
29
229.4
0.242846
07
32. 18
0*42237E
04
0.18243E-02
0.649E-04
23.
30
232.0
0-2457 8E
07
32.53
Ci42777E
04
0.1E463E-02
0.681 E-04
23-
31
234.6
0.248J2E
0 7
32.53
0*43^3146
04
0. 1809 8E-02
0.664E-04
23.
32
237.3
0.25167E
07
32. 20
0143 850E
04
0.18325E-02
0.662E-04
23.
33
239-9
0-25462E
07
32.32
0*443 84E
04
0.18064E-02
0.664E-04
23.
34
242.5
0.25755E
07
22.07
0144916E
04
0.18076E-02
0.643 E-04
23.
35
245.1
0.26049E
07
32. 28
C 1454460
04
0.18039E-02
0.679 E-04
23.
36
247.8
0.26343E
07
22.05
0 145972E
04
0.17720E-02
0.720E-04
23.
UNCERTAINTY IN REX=2;8506- UNCERTAINTY IN F=0. 05034 IN RATIO
151
PUN
121474
*0*
DISCRETE
HOLE RIG *** NAS-3- 1433A
STANTOM
NUMB'^R
OA TA
**♦ 2900STEP40 P=C.4
TH=0
P/C=10
kit-k
RUN
121274-2
*+*
DISCRETE
HOLE RI€ **♦ NAS-3-14336
STANTON
NUMBER
CATA
2 900STEP40 M=0;4
Th=l
P/0 = 10
LINEAR SUPERPOSITION IS APPLIED TO STANTON NUMBER CATA
FROM
PUN NUMBERS 12U74 AND 121274-2 TO OBTAIN STA^TC^ ^UMBeP CAT^ iT t H=? AND TH=1
PLATE
RE XCOL
RE DEL2
ST(TH=0)
REXHOT
RE DEL2
ST(TH=1I
ETA
ST CO
F-COL
STH'J
L0r,3
1
1294474. 0
103.1
0.003598
1267625.0
96.5
C. 003456
UUUUU
1.007
0.3003
0. 967
0. 333J
3.967
2
1351789.0
290.7
0. 002947
1344638.0
274.0
0.002701
0.084
0,780
0.0032
6,930
0.0026
1.431
3
1409105.0
455.2
0.002794
1401650.0
5 eo.4
0.002413
0.136
0. 827
0.0032
Q.931
0.0028
1.404
4
1466421.0
609.5
0.C02589
1458662.0
373.7
0.002244
0.133
0.626
0.0031
0.902
0.0029
1.397
5
1523736.0
758.4
0.002609
1515675.0
1159.2
0.002067
0.208
0.880
0.0031
0.B57
0.0029
1.364
6
1581052.0
903.4
O.C02450
1572687.0
1438.0
0.002008
0.183
J.863
0.0032
0.855
0. 0031
1.419
7
1638367.0
1044.4
0.002471
U29700.0
1730.1
C.C0195S
0.207
0.903
0.0032
0.B5 2
0.0031
1.428
8
1695683.0
1 1 83 . 3
0.002376
1686712.0
2019.4
0.001914
0.194
3,896
0. 0031
C.849
0. 3027
1.356
9
1752999.0
1319.5
0.C02375
1743725.0
22 7 7.6
0.001808
0i239
0.921
0.0031
0.815
0.0027
1.328
10
1810314.0
1453.5
0.002303
1800737.0
2532.6
C.00179C
0.223
0.915
0.0032
C.820
0. 3031
1.417
11
1667630.0
1585.3
0. C02297
1857749.0
2811.6
0.001743
0.242
0.933
0,0032
0 . B09
0.0031
1.413
12
1924946.0
1714.6
0.002212
1914762.0
3087.9
0.001696
0*233
0.916
0.0033
0.798
0.0029
1.376
13
1968506.0
1811.9
0.C02292
1958091.0
3329.4
C. 001718
0*250
0.963
0.816
14
1998023.0
1879.1
0.002258
1987453.0
3548.4
0.001760
Oi221
0.957
B.B41
15
2027541.0
1945.5
0.002237
2016814,0
3600.6
0.001790
0.200
0.956
Q.860
16
2057201.0
2011.2
0.002209
2046318.0
3653.2
0.001790
0*190
0.952
0.865
17
2086862.0
2076.3
0.002198
2075822.0
3705.9
0.001797
0*183
0.955
0.873
18
2116380.0
2140.8
0.XJ02165
2105183.0
3758.8
0.001800
0.169
0.948
0.879
19
2145897.0
2204.3
0.002128
2134545.0
3811.6
0.001794
0*157
0.939
0.881
20
2175415.0
2267.5
0.002152
21639C6.0
3864.7
0.001817
0*156
0.956
0.896
21
2204933.0
2330.6
0.0.02118
2193268.0
3917.7
0,001792
0*154
0. 947
0.888
22
2234450,0
2392.9
0.002097
2222629.0
3970.4
C. 001795
0*144
0.944
0.894
23
2263968.0
2454,0
0.002042
2251990.0
4023.0
0,001783
0*127
0.926
0.892
24
2293628.0
2514.6
0.002059
2281494.0
4075.0
0.001753
0*149
0.939
0.881
25
2323289.0
2575.8
0.002083
2310998.0
4127.6
0.001825
0*124
0.956
0.921
26
2352607.0
2637.4
0.002063
2340359.0
4180.9
0.001603
0*134
0.962
0.914
27
2382324.0
2698.9
0.002083
2*369721.0
4233.2
0. 001757
0*157
0.967
9.894
28
2411842.0
2760.4
0.002C77
2399082.0
4285.6
0.001806
0*131
0.970
0.923
29
2441360.0
282T.8
0.^002078
2428444.0
433 8.5
0.001799
0il35
0.976
0.923
30
2470877,0
2883.3
0.002080
2457805.0
4391.8
0.001823
0*124
0.982
0.939
21
2500395.0
2944.2
0.002046
2487167.0
4444. 8
0.001786
0*127
0.971
S.923
32
2530056.0
3004 .0
0.00 200 2
2516670.0
4497.7
0.001815
0*093
0.955
S.942
33
2559716.0
3063.8
0.002040
2546174.0
4550.6
0.001783
0*126
0.978
Q.92B
34
2589234.0
3123.6
0.002010
2575536.0
4603.1
0.001787
0ill2
0.970
8.934
35
2618752. 0
3182.9
0.001995
2604897.0
4655.6
0.001784
0*196
0.966
0.936
36
2648269.0
3241.3
0.001961
2634258.0
4707.6
0.001753
0*106
0.953
0.923
STAirrCN NUMBER RATIO BASED ON ST«PR««0.4>0«0295*REX**<-.2l*ll.-(XI/(X*XVOn**0.9)**(-l./9.)
STAMTON NUNBER RATIO FOR TH>1 t$ CENVERTEO TO COMPARABLE TRANSPIRATION VALUE
VttHS ALOOfl * Bl/B EXPRESSION IN THE BLOWN SEaiCN
RUN 12167V1 *** DISCRETE HOLE RIG NAS-3- 14336
STANTON NUMBER DATA
TACe=
20.15
DEO C
UINF
16.6 5 P/S
TINF= 20*03
DEG C
FH0=
1. 206
KG/M3
V ISC
= 0. 149576-04 M2/S
XVC= 13.0
CM
CP=
1011.
J/KGK
PR =
0i716
2900STEP75 M=G
1.75
o
II
X
1-
F/0=10 ***
PLATE
X
REX
TO
PEE NTH
STANTON NO
OST
OREEN
M
6
T2
THFTA
DTH
1
127.8
0.12775E
07
30-79
0il0311E
03
0. 364596-02
0.7996-04
2.
2
132.8
0.13340E
07
30. 79
01290606
03
0.258376-02
0.741E-04
6.
0.78
0.0063
20*92
0.083
0 .02 8
137.9
0. 13906E
07
30. £2
0148 861E
03
0. 297176-02
0.738E-04
10.
0.00
0.0063
30182
0.083
0.029
4
143.0
0.14471E
0 7
20. 80
0*680576
03
0.27694E-02
0.723E-04
13.
0.78
0.0063
21*10
0.099
0.028
5
148.1
0.150376
07
30.82
01872806
03
0.277346-02
0.722E-04
15.
0.00
0.0063
30182
0.099
0.029
6
153.2
0.15603E
07
30. £0
0il0591E
04
0. 255916-02
0.707 e-04
17.
0.78
0.0063
21*09
0.098
0.028
7
158-2
0.16168E
07
30.80
0U2415E
04
0.264536-02
0. 7136- 04
19.
0.00
0.0063
30*80
0.098
0.029
8
163-3
0. 1673 4E
07
3 0.79
01142236
04
0. 250236-02
0.7046-04
20.
0.78
0.0063
21124
0.112
0.02 8
9
168.4
0. 17299E
07
30.79
0116041E
04
0.251076-02
0.7056-04
22.
0.00
0.0063
30179
0.112
0.029
10
173-5
0. 17865E
07
30. 80
Qil78316
04
0. 239786-02
0.6956-04
23.
0.78
0.0063
21122
0.110
0.026
11
178.6
0. 18431C
07
30. 80
C119595E
04
0.24447E-02
0. 6996-04
25.
0.00
0.0063
30180
0.110
0.029
12
183.6
0. 13996E
07
30.80
0i21348E
04
0.235456-02
0.692E-04
26.
0.78
0.0063
21126
0.114
0.028
13
187.5
0.19426E
07
30. 52
C^22777E
04
0.243956-02
0. 8676-04
26.
14
190.1
0.1971 76
07
30. 38
0123892E
04
0.24120E-02
0.871E-04
26.
15
192.7
0.20009E
0 7
30.73
01245926
04
0. 238616-02
0.8736-04
27.
16
195.4
0.203016
07
30.75
01252826
04
0.224866-02
0. 849E-04
27.
17
198.0
0.20 5 94E
07
30. 77
01259656
04
0.233776-02
0.848 E-04
27.
18
200.6
0. 208856
07
'30.73
0126645E
04
0.222346-02
0.8436-04
27.
19
20 3.2
0.21177E
07
30. 71
0*273166
04
0.22763E-02
0.820 E-04
27.
20
205.8
0.21468E
07
30. 79
0*279836
04
0.220146-02
0. 8336-04
27.
21
208.5
0.217596
07
30.71
0*286506
04
0.22713E-02
0. 8176-04
27.
22
211.1
C-22051E
07
30. 80
C*2930£E
04
0.224206-02
0.8246-04
27.
23
213.7
0.22342E
07
30.73
0*299546
04
0.218496-02
0.806E-04
27.
24
216.3
3.226356
07
30. 56
0*305946
04
0.220396-02
0.8016-04
27.
25
218.9
0.229276
0 7
30.73
0*312406
04
0.2228QE-02
0. 8236-04
27.
26
221.6
0. 23219E
0 7
30.69
O*31809E
04
0.221986-02
0.8536-04
27.
27
224.2
0.23510E
07
29.64
01325356
04
0. 221586-02
0.768E-04
27.
28
226.8
0.238016
07
30.71
0*331836
04
0.22253E-02
0.859E-04
27.
29
229.4
0.2 409 3E
07
30.65
0*338296
04
0.2203 lE-02
0.7926-04
27.
30
232.0
0. 243846
07
31.00
0*344776
04
0.22393E-02
0.8296-04
27.
31
234.6
0.24675E
07
31.02
0*351206
04
0.2175QE-02
0.8006-04
27.
32
237.3
0.24968E
07
30.86
01357526
04
0.215886-02
0.791E-04
28.
33
239.9
0.25 26 IE
07
30- 82
0*36386E
04
0.21851F- C2
0.8066-04
28.
34
242.5
0.25 5526
07
30. 57
0*370216
04
0.217006-02
0.7806-04
28.
35
245.1
0.2584 36
07
30.77
C137652E
04
0. 215656-02
0.8166-04
28.
36
247.8
0.26134E
07
30.56
01382726
04
0. 209696-02
0.860E-04
28.
UNCERTAINTY IN R6X=28281.
UNCERTAINTY IN F=C.C5035 IN RATIO
153
RUN 121674-2 ***' CISCRETE HCLE RIG *** NAS-3-14336
STANTCN NUMBER DATA
TAOe=
RFC =
CP =
19.63
1.208
1011.
CEG C
KG/M3
J/KGK
UIMF= 16.64
VISC= 0.14911E-04
PP.= 0i716
M/S
M2/S
T INF=
XVC =
19.51
13.0
DEG C
CM
2900STEP75
M=0. 75 7H-1 P/n*lO
***
PLATE X
REX
TO
REE NTH
STANTCN NO
CST
OREEN
H
F
T2
THEFA
DTM
1
127.8
0. 12802E
07
31.55
0;97654E
02
0.34456E-02
0.702E-04
2.
2
132.6
0.13369E
07
31. S7
Oi27431E
03
0.27876E-02
0.650E-04
10.
0.74
0.0060
31181
1.020
0.026
3
137.9
0.13936E
07
.31.55
Oi77672E
03
0.27609E-02
0.649E-04
17.
0.00
0.0060
3U55
1.020
0.026
4
143.0
0.14 5O2E
07
31. 59
Q*12712E
04
0.25065E-02
0.630E-04
22.
0.75
0.0060
31159
1.000
0.026
5
143.1
0-15069E
07
31.57
Cil7526E
04
0.2425 4E-02
0.625E-04
26.
0.00
0.0060
31157
1.000
0.026
6
153.2
0.15636E
07
31. 57
0i22264E
04
0.224C6E-02
0.614E-04
BO-
0.76
0.0061
31155
0-998
0.026
7
158.2
0.162S3E
07
31.55
Ci26994E
04
0.2204 7E-02
0.612E-04
SS.
0.00
0.0061
31*55
0.998
0.026
8
163.3
0- 16770E
07
21.57
0.31690E
04
0.21202E-02
0.606E-04
36.
0.75
0.0061
31148
0.992
0.026
9
168.4
0.17336E
07
31. 59
Q*36327E
04
0.213 89E- 02
0.607E-04
39.
0.00
0.0061
31159
0.992
0.026
10
173.5
0.17903E
07
21 .59
0*40946E
04
0.20576E-02
0.602E-04
41.
0.75
0.0061
31114
0.963
0.026
11
178.6
C- 18470E
07
31. C3
C*45434E
04
0.20545E-02
0.600E-04
43.
0.00
0.0061
31163
0.963
0. 026
12
163.6
0.19037E
07
31.61
0.49901E
04
0.1S8 79E-02
0.597E-04
45.
0.77
0.0062
30192
0.943
0.025
13
187.5
0.19468E
07
31.20
Oi54Q80E
04
0.20977E-02
0.742E-04
46.
14
190.1
0. 19760E
07
21-09
Oi58006E
04
0.21306E-02
0.759E-04
46.
15
192.7
0. 2005 2E
07
31.44
C-58625E
04
0.21065E-02
0.766E-04
46.
16
195.4
0.20345E
07
21.44
0.59240E
04
0.21043E-02
0.753E-04
46.
17
198.0
0.20638E
07
31.46
X3.59855E
04
0.20993E-02
0.754E-04
46.
IB
200.6
0.20930E
07
31.44
Ci60464E
04
0.2C72 8E-02
0.746E-04
46.
19
203.2
0.21222E
07
21.42
0161066E
04
0.20414E-02
0.729E-04
46.
20
205.8
0.21514E
07
31.44
C161670E
04
0.2C935E-02
0.747E-04
47.
21
206.5
Q.21806E
07
31.42
Oi62272E
04
0.20274E-02
0.725E-04
47.
22
211.1
0.22098E
07
21.47
0^62 E65E
04
0.20275E-02
0.738E-04
47.
23
213.7
0. 223.90 E
07
21.36
0^63452E
04
0. 199 36E-02
0.723E-04
47.
24
216.3
0.22683E
07
31. 28
G164031E
04
0.19642E-02
0.713E-04
47.
25
218.9
0.22976E
07
21.36
01646 15E
04
0.2C366E-02
0.741E-04
47.
26
221.6
0.23268E
07
21.34
0165207E
04
0.20105E-02
0.764E-04
47.
27
224.2
0.2356 0E
07
30. 33
C165788E
04
0.19648E-02
0.672E-04
47.
28
226.8
0.23852E
07
31.36
0*66370E
04
0.20212E-02
0.771E-04
47.
29
229.4
0.24144E
07
31.20
Q166956E
04
0.19891E-C2
0.708 E- 04
47.
30
232.0
0.24436E
07
21.63
QA67544E
04
0.20371E-02
0.747 E-04
47.
31
234.6
0. 24728E
07
31.65
0168132E
04
0* 198 39E-02
0.724E-04
47.
32
237-3
0.2502 IE
07
21.44
0168709E
04
0.19645E-02
0.715E-04
47.
33
239.9
0-25315E
07
21. 3C
0169292E
04
0.20265E-02
0.732E-04
47.
34
242.5
0. 25607E
07
21.19
0169874E
04
0-19535E-02
0.699E-04
47.
35
245.1
0.25898E
07
21.40
0470446E
04
0 .196146-02
0.734E-04
47.
36
247.8
0.26190E
07
31.21
<U71012E
04
0.19144E-02
0.774E-04
47.
UNCERTAINTY IN REX=2 8341.
UNCERTAINTY IN F»-0. 05035 IN RATIO
trSl
RUN
121674-1 *4* DISCRETE HOLE R16 *** NAS-3- 14236
STANTON NLMBER DATA
**♦ 2900STEP75 R=C.7S TH=D P/D=XO ***
RUN
121674-2
*** 01 SC RET
E HCLE RI G
NAS-3-14336
STANTCN
NUMBER
DATA
2900STEP75 M=
0.75 TH=
1 P/D=lb
LINEAR SUPERPO
jITION I.S APRLIEC to STANTON NUMBER
CATA FROM
RUN
NUMBERS 121674-1 A NO
121674-2 TO
DETAIN STANTCN NUMBER
CATA AT 7
H=0 AND
II
I
PLATE
RFXCOL
RE CEL2
ST(TH=OJ
REXHOT 0 E
DEL2 ST(TH=U
FTA
STCP
F-COL
STHR
= -Hor
LDG8
1
127745 1. 0
103 .1
0, C03646
1280184.0
9 7.7
C. 005446
UU'J'JU
1.020
0.0000
Q. 964
0, 300)
0,964
2
1334013,0
291 . 1
0. CG30G1
1 336867.0
274.4
0.002792
0.070
0.792
0.0063
1.012
0,0060
1.892
3
1390575. 0
460.5
0.C02990
1393550,0
770. 3
0.002765
0 .0 75
0,803
0.0065
1.065
0.006)
2.300
4
1^^47137. 0
624.2
0. C02795
1450233.0
12 58.2
C. C02509
0 .102
0.8 90
0.0063
1.007
0.0060
1.976
5
1503699.0
782.7
0.C02812
1506916.0
1739.7
0.002425
0.137
0. 946
0.0063
1.005
0.0060
2,000
6
1560261.0
935.6
0. 002594
1563599.)
2213.6
C. 002240
0.136
0.912
0.0063
0.952
0.0061
1.977
7
1616£23. 0
1085 .2
0.002693
1620282.0
2687.2
0.002204
0.182
0. 982
0.0063
0.95B
0,0061
2,003
8
1673385. 0
1233.4
0. C02547
1676965.0
3157.3
0. J)2118
0.168
0,959
0.0063
C.938
0.0 061
1.993
9
1729947.0
1377,8
0. 002558
1733648.0
3623.5
C. 002136
0.165
0.939
0.0063
0.962
0.0061
2 .036
10
17865G8. 0
1519.1
0.C02441
1790331.0
40 37. a
0.0)2049
7.161
0.967
0.0063
C.937
0.0 061
2.019
11
1843070.0
1658.8
0.C02495
1 847C14.0
4548. 6
U. 002036
0.193
l.OU
0.0063
0.945
0.0061
2.042
12
1899632. 0
1797.3
3. C02403
1902697.0
5097.1
0.0)1967
0 .181
0,993
0.0063
0.925
0.0 062
2.046
li
1942620.0
1901 .5
0. C02485
1946776.0
5444.2
C. 0)2079
0.164
1.041
0.986
14
1 971 749.0
1973.5
0.C02449
1975968.0
535b. 3
0.00211 5
0.137
1.035
1.009
15
2000878,0
2044.5
0.002-423
2005160.0
591 7. e
0.0)2091
0.137
1.033
1.004
16
2030149. 0
2114.6
0 .CO 2381
2034493.0
59 7 8. 9
0.002091
Oi 122
1. 024
1 . 009
17
205942C.O
2183.8
). C023 70
2063826.0
6039.9
0.002)86
0 .120
1. )27
1.012
IB
2088549.0
2252.8
0.002357
2093018.0
61C0.5
0.002059
0. 126
1.029
1.004
19
211 7678. 0
2320.8
0. C023C8
2122210.0
6160,2
0- 0)2)2 8
0.121
1.015
0.995
20
2146808. 0
2388.4
0.002329
21514C1. 0
6220. 3
0. 0)2082
0.106
1.032
1.026
21
2175938. 0
2456 .0
0, C02304
2180593.0
6280.1
0.002014
0 ,126
1.028
0. 997
22
2205C67. 0
2 5 22 .7
0. CC2271
22C9785. 0
6339. C
0,003 015
0-112
1,0 20
1.003
23
2234196. 0
2588 ,0
0.002210
2238977.0
639 7.4
G. 001933
0.103
0.999
0.991
24
2263467. 0
2652. 8
0. C02236
2268310.0
6454. 9
0.001951
0.123
1.017
0,979
25
2292738.0
2718 .3
O.C02254
2297643.0
6513.0
G. 002026
0.101
1.032
1.021
26
2321 867. 0
2783.9
0. 002248
2326835.0
6571.8
0.) U999
0.111
1.035
1.012
27
2350996.0
2 849. . 5
0.002249
2356027.0
6629.6
0. 001951
0. 133
1.042
0.992
28
2380126. 0
2915.2
0.002253
2385218.0
6687.4
0.0 )2)10
0. 108
1.049
1.026
29
2409256.0
2980.5
0.002232
2A14411 .0
6745. 7
C. 001977
0.114
1.045
1.013
30
2438385.0
3046 .1
0.002266
2443602.0
6604.2
C. 002026
0*106
1.067
1.042
31
2467514. 0
3111.3
C. CG22CI
2472794.0
6662.6
0.001973
0.104
1.042
1.019
32
2496785.0
3175.2
O.C02185
2502127.0
6920.0
0.001954
0*106
1. 039
1.013
33
2526C56. 0
3 239.2
0.CO22C6
2531461.0
6978. C
0.00201 8
0.035
1.055
1.050
34
2555185. C
3303.5
0.002199
2560652.0 '
7035.9
0.001941
0.117
1, )56
1.014
35
2584314.0
3367.4
0.C02185
25B9844.0
7092. 8
C. 001950
0-107
1,055
1.022
36
2613444.0
3430.2
0.C02121
2619036.0
7149. 1
0.001904
0 . 1 02
1.029
1.001
STANTCN NUPaER RATIO 0ASEC ON ST*J>P+*0 .4=0 .029 5*R E>** (- . 2 »*( 1 ( X I / ( X-XVO ) ) *^0 .9 ) **( - 1. /9. )
STANTON NUHBEP PATIO F CR TH=1 IS CGNVERTED TO CORPARABLE TRANSPIRATION VALJE
LSING ALOGd + B)/3 EXPRESSION IN THE BLOWN SECTION
RUN 092074 VELGCnV PROFILE
REX = 0.74658E 06
XVO = 10.07 CR.
UINF = 9.78 M/S
Vise = 0.15419E-04 M2/S
PORT = 9
XLOC = 127.76 CP.
REH = 1648.
DEL2 = 0.291 CM
DEL99C 2.408 CM
OELl « 0.410 CM
H = 1.407
CF/2 * 0.18480E-02
Y(CM. J
Y/OEL
U(M/S)
0.025
0.011
3.3 1
0.028
0.012
3.42
0.030
0.013
3.57
0.033
0.014
3.63
0.038
0.016
4.01
0.046
0.019
4.35
0.056
0.023
4.79
0.C69
0.028
5.09
0.084
0.035
5.38
0. 102
0.042
5.58
0. 122
0.051
5.79
0. 145
0.060
5-91
0.170
0.071
6.15
0.201
0.083
6.27
0.236
0.098
6.38
0.277
0.115
6.53
0.323
0. 134
6.71
0.373
0.155
6.86
0.437
0. 181
6.98
0.513
0.213
7.16
0.615
0.255
7.40
0.742
0.308
7.64
0.894
0.371
7.95
1.046
0.435
8.17
1.199
0.498
8.40
1.351
0.561
8.63
1.504
0.624
8.66
1.656
0.688
9.03
1.808
0.751
9.21
1.961
0.814
9.38
2. 113
0.878
9.50
2.266
0.941
9.62
2.418
1.004
9.71
2. 57C
1.067
9.75
2.723
1.131
9-78
U/UINF
y +
U+
0.338
6,9
7.87
0.350
7.6
8.14
0.365
8.3
8. 50
C.371
9.0
8.63
0.410
10.4
9,54
C.444
12.5
10.34
0.489
15.2
11.38
0.520
18. 7
12.10
C.550
22.9
12.80
G.570
27.7
13.26
0,592
33.2
13.78
0.604
39-5
14,05
0.629
46.4
14.64
0.641
54.7
14.91
0.652
64.4
15.18
C.667
75.5
15.52
0.686
88.0
15.95
C.701
101.8
16.31
0.714
119.1
16.61
0.732
139.9
17.03
0.756
167.6
17.59
C.781
202.3
18.16
0.813
243.8
18.91
C.835
285.4
19,44
0.859
326.9
19.98
0.682
368.5
20.52
0.906
410.1
21.0b
0.923
451.6
21,48
0.942
493 .2
21.91
0.959
534.7
22.31
0.971
576.3
22.60
0.963
617.8
22.67
0-992
659.4
23.08
C.997
701.0
23.20
1.000
742.5
23.26
RUN 092074 DISCRSTE HOLE RIC NAS-3-14336
STANTON NUMBER DATA
TACB=
23,61
DEG C
UINF
~
9.7? M/S
TINFaa 23.57
OEG C
RHQ=
1, 177
KG/M3
»/ ISC
- 0.15419E-04 M2/S
XVO= 3.6
CM
CP =
10l5o
J/KGK
PR =
0 J717
j)t \a ^
I900STEPFP P/D =5
si-
PLATE
X
REX
TO
PEENTH
STANTON NO
DST
DREEN
ST(TH60>
RATi;
1
12 7«8
Q.78737E
06
37.16
Qi65659E
02
0.407 78 E-02
0.118E-03
2.
3. 34758E-02
1.173
2
132,8
C.ei9S 8E
06
37. 20
Oil8 7 24E
03
0.3473 IE -02
0. 109^03
3 .
0.30647E-02
1. 133
3
137.9
0. 85 178E
06
37. 2C
0-29626E
03
0- 229 7 66-02
0.107E-03
4,
0.28851E- 02
1.143
4
143-0
0.83398E
06
37. 16
Ci4CC8lE
03
0.31954E-C2
0.106E-03
5.
0*276966-02
1.154
5
148.1
0.91619E
06
37, 18
0.50159E
03
0,206366-02
0.1046-03
5,
0. 268426-02
1.141
6
153.2
0. 94839E
06
27, 20
C 1598336
03
0.294476-02
0.102E-03
6.
0. 261656-02
1.125
7
150.2
0.93059E
06
37.18
0169291E
03
0.29288E-02
0.102E-03
6.
0.256046-02
1.144
8
163-3
0- 101,2 8E
07
37. 16
01785856
03
0.28434E-02
O.lOlE-03
7.
0. 251236-02
1.132
9
168,4
0. 10450E
07
37. 16
0*87605E
03
0. 275866-02
O.lOOE-03
7.
0.247046-02
1.117
iO
173-5
0. 107726
07
27.16
0i96433F
03
0.27241E-02
0.999E-04
7.
0.243316-02
1.120
11
178.6
0.11 09 4E
01
37. 16
Ca05C7E
04
0.26396E-02
0.989E-04
8.
0.239956-02
1.100
12
183.6
0. 11416E
07
37.20
0U1354E
04
0.26182E-02
0.985 E-C4
8.
0.236906-02
1.105
13
187.5
0.11661E
07
37.11
0411987E
04
0.25477E-02
0.102E-03
8.
0.234 76 E-02
1.085
14
190.1
0.1182 7E
07
37.07
0U2406E
04
0.250456-02
0.103E-03
8.
0.233386-02
1.073
15
192,7
0. 11993E
07
27. 37
Ca2814E
04
0. 24022E-02
G.lOOE-03
9.
0.232056-02
1.035
16
195 .4
0.12159E
07
27.25
0il2211E
04
0.23899E-02
0.983E-C4
9.
0.230776-02
1.036
17
19 8,0
0. 123266
07
37.23
0^136096
04
0.23935E-02
0.985E-04
9,
0.229546-02
1.043
18
200o6
0. 12492E
07
37.33
04140046
04
0.23647E-02
0.978E-04
9.
0.228356-02
1.036
19
203.2
0.12658E
07
37, 31
Cil4393E
04
0.23299E-02
0.951E-04
9-
0. 227216-02
1.025
20
20 5.8
0.12 823E
07
37.43
0-14781E
04
0.234106-02
0.964E-04
9.
0.226106-02
1.035
21
208.5
0. 12989E
07
27. 27
041516TE
04
0.23024E-02
0.943E-04
9.
0.225036-02
1.023
22
211.1
0.13155E
07
27-45
04155476
04
0.228176-02
0- 956E- 04
9.
0.22399 E-02
1.019
23
213. 7
0.13321E
07
37. 39
0-159246
04
0.22546E-02
0.935E-04
9-
0.222986-02
1.011
24
216.3
0, 13488E
07
37.49
04163016
04
O.22834E-02
0.962E-04
9.
0.22200 6-02
1,029
25
218.9
0. 13654E
07
37.43
0^166786
04
0.22599E-02
0.9466-C4
9.
0. 221046-02
1.022
26
221.6
0. 1382 06
07
37.31
04170516
04
0.223 806-02
0.983E-04
9.
0.2201 2 E-02
1.017
27
224.2
0. 13986E
07
26.31
0*174326
04
0 .234256-02
0.913E-04
9.
0.219226-02
1.069
28
226,8
0. 1415 2E
07
37.27
04178096
04
0,220716-02
0.982E-04
9 .
0.21835E-02
1,011
29
229.4
0.14318E
07
37. 30
0-18179E
04
0.22524E-02
0.919E-04
10.
0.21749E-02
1.036
3C
232. C
0. 14483E
07
27.6 8
Q. 185516
04
3.22182E-02
0.949E-04
13.
0.21666E-02
1.024
31
234.6
C. 14649E
07
37, 68
0.189176
04
0. 2 18 886-02
0- 9226-04
10.
0.215856-02
1.014
32
237.3
0.14816E
07
37. 56
0*19 2786
04
0.21700E-02
0,9156-04
10.
3.21506E-02
1.009
33
239.9
0.149826
07
37. 51
C.19640E
04
0, 213736- C2
C. 9226-04
10.
0.21428E-02
1.021
3A
242.5
0. 15 14 31'
07
37. 30
C .200026
04
0. 21705:— 02
0.891F-C4
10,
0.21352E-02
1.017
35
245.1
•». 15 21 42
0 7
37. 49
0.203596
04
0.2133 EE-02
0.937F-04
10.
0.21278B-02
1.003
36
247.8
0. 1543 Jc
0 7
37. 14
G .207126
04
0 .211106-02
0.1026-03
10.
0.21206r-02
0.995
RUN C92274-1 DISCRETE HOLE RIE ♦** NAS-3-14336
STANTGM NUMBER DATA
TACe =
' 21.22
DEG C
UINF
■=
9.79 M/S
TINF= 21,18
DEG C
RHO =
1. 183
KG/M3
V ISC
:= 0.15274E-04 H2/S
XVC= 3.6
CM
CP =
1012.
J/KGK
PR=
0i716
***
1900STEP40 M=C
1.4
TH = C
P/0=»5
PLATE
X
REX
TO
P6ENTH
STANTCN NO
DST
OREEN
M
F
12
THETA
0T^
1
127.8
0.79629E
06
35.^1
0.69342E
02
0.^2583E-02
0.116E-03
2.
2
132.8
C.E2 8B6E
06
35.41
0il9786C
03
O.36340E-O2
0.1076-03
6.
0.40
0.0128
22106
0.062
0.02 2
2
137.9
0.86143E
06
35.39
C1339C7E
03
0.344 6 9E-02
0.105E-03
9.
0.39
0.0127
22149
0.092
0.021
4
143.0
0.89400E
06
35.35
0.48597E
03
0.32402E-02
0.102E-03
11.
0.39
0.0127
22140
0.086
0.022
5
148.1
0.92657E
06
35.39
0i62539E
03
0.313 05t-02
O.lOlE-03
13.
0.39
0.0127
22139
0.085
0.022
6
153.2
0.95913E
06
35.37
Q.76C94E
03
0.30295E-02
0.997E-04
15.
0.38
0.0123
22142
0.088
0.022
7
158.2
0.99 170E
06
35.37
0A89393E
03
0.29796E-02
0.991E-C4
16.
0.39
0.0125
22156
0.098
0.021
8
163.3
0.10243E
07
35.39
0110295E
04
0.29006E-02
0.9 81E-04
18.
0.39
0.0126
22154
0.096
0.021
9
168.4
0.1056EE
07
35.37
011162OE
04
0.2e074E-02
0.9716-04
19.
0,39
0.0125
22155
0.097
0.021
10
173.5
0. 10894E
07
'35.35
0a293CE
04
0.26207^-02
0.973E-04
20.
0.37
0.0121
22157
0.098
0.022
11
178.6
0,11220E
07
35. 35
C*14228E
04
0.27642E-02
0.967E-04
21.
0.39
0.0126
22158
0.099
0.022
X2
183.6
0.11S45E
07
35.35
C.155C7E
04
0.25825E-02
0.946E-04
22.
0.39
0.0125
22158
0.099
0.022
13
1E7.5
0.11793E
07
34.93
Oil6550E
04
0.261B1B-02
0.102E-03
23.
14
190.1
0.1196 IE
07
34.95
0il6974E
04
0.243 02E-02
0.995E-04
23.
15
192.7
0.12128E
07
35.30
0U7371E
04
0.23014E-02
0.957E-04
23.
16
195.4
0.12 297E
07
35.30
0il7755E
04
0.22682E-C2
0.930E-04
23.
17
198.0
0.12445E
07
35. 31
0il8134E
04
0.22405E-02
0.922E-04
23.
18
200.6
0. 12633E
07
35.33
0U8505E
04
0.21774E-02
0.903E-04
23.
19
203.2
0. 128,0 IE
07
35.35
0*18864E
04
0.21093E-02
0.867E-04
23.
20
205.8
0.12969E
07
35.47
0119219E
04
0.21075E-02
0.872E-04
23.
21
208.5
0.13136E
07
35,^5
Ca9568E
04
0.2C52 6E-02
0.849 e-04
23.
22
211.1
0.13304E
07
35.52
0a9910E
04
0.202516-02
0.857E-04
23.
23
213.7
0. 13472E
07
35.49
0*2 0247E
04
0.19832E-02
0.833 E-04
23.
24
216.3
0.13640E
07
35. 58
CA20581E
04
0.19965E-02
0.8 53 E-04
23.
25
218.9
0.13609E
07
35.52
Oi209I2E
04
0.194 85E-02
0.831E-04
23.
26
221.6
0. 13977E
07
35.39
0J21242E
04
0.19786E-02
0.6 78 E-04
23,
27
224.2
0.14144E
07
34. 46
0121581E
04
0.2054 4E-02
0.813E-04
23.
28
226.8
0.14312E
07
35.47
0.21916E
04
0.193 73E-02
0.8 74 E-04
23.
29
229.4
0.14480E
07
35. 39
Oi22246E
04
0.19939E-02
0.822E-04
23.
30
232.0
0.14648E
07
35.75
0122578E
04
0.19572E-02
0.849E-04
23.
31
234.6
0. 1481 5E
07
35.75
0122904F
04
0.19362E-02
0.825 E-04
23.
32
237.3
0. 1498 4E
07
35.66
Oi23229E
04
0. 19287E-02
0.824E-04
23.
33
239.9
0.15152E
07
35.60
0123554E
04
0.19457E-02
0.829E-04
23.
34
242.5
0-1S320E
07
25.39
0123879E
04
0.191 84E-02
0.799E-04
23.
35
245.1
0. 15488E
07
35.52
0424200E
04
0.19044E-02
0.8486-04
23.
36
247.8
0.15656E
07
25. 16
Q124518E
04
Q.18S2 8E-02
0.935E-04
23.
UNCERTAINTY IN REX*16284. UNCERTAINTY IN F»0.05295 IN RATIO
8UN 092274-2 DISCRETE HCLE BIS **♦ NAS-3- 14336 STANTON NWBER DATA
TAO!fi*
21.74
OEG C
UINF
=
9.82 H/S
TINF- 11.70
DEG C
RHOf
1.181
K6/H3
Vise
» 0.15321E-04 M2/S
XVO« 3.6
CM
CP»
1013.
J/KGK
PR-
01716
***
1900STEP40 H=0.4
TH»1
P/0«5
PLATE
X
REX
TO
■REENTH
STANTON NO
OST
DREEN
M
F
T2
THETA
DTH
1
127.8
0.79e/»8E
06
38.10
0163026E
02
0.3eT0X)E-02
0. 102E-03
2 .
2
132.8
0.82895E
06
38.10
0117452E
03
0.29760E-02
0.894E-04
10.
0.35
0.0115
36i65
0.912
0.019
3
137.9
0.86152E
06
38. 11
0160502E
03
0.25316E-02
0.840E-04
18.
0.37
0.0121
37121
0.945
0.019
4
143.0
0.89409E
06
38.11
0il0531E
04
0.21143E-02
0.796E-04
23.
0.36
0.0117
37130
0.950
0.019
5
148.1
0.92666E
06
38. 11
0114825E
04
0.l974«E-02
0.782E-04
27.
0.36
0.0115
37113
0.940
0.019
6
153.2
0.95924E
06
38.11
Oil 896 3E
04
0.17865E-02
0.765E-04
31.
0.36
0.0118
37100
0.932
0.019
7
158.2
0.99181E
06
38. 11
0123123E
04
0.17732E-02
0.764E-04
34.
0.B2
0.0103
36194
0.926
0.019
8
163.3
0.10244E
07
38.11
0126804E
04
0.169 eSE- 02
0.757E-04
36.
0.32
0.0105
37185
0.984
0.019
9
168.4
0.10570E
07
38.13
0130698E
04
0.160BSE-02
0.749E-04
39.
0.33
0.0106
37115
0.940
0.019
10
173.5
0.108^5E
07
38. 13
0 134445E
04
0.15580E-02
0.745E-04
41,
0. 37
0.0120
36167
0.911
0.019
11
178.6
0.H221E
07
38. 15
0i38513E
04
0.15116E-02
0.741E-04
43.
0.32
0.0105
36153
0.901
0.019
12
183.6
0.11 54 7E
07
B8.19
0142 066E
04
0.140A2E-02
0.731E-04
45.
0,37
0.0120
36156
0.901
0.018
13
1E7.5
0.11794E
07
37. 83
0*45 936E
04
0.152 12 E-02
0.637E-04
46.
14
190.1
0.11962E
07
37.73
0146191E
04
0.15103E-02
0.665E-04
46.
15
192.7
0.12130E
07
38. C6
0*46437E
04
0.14265F-02
0.643E-04
46.
16
195.4
0.12 29 8E
07
38. 06
0146678E
04
0.14351E-02
0.633E-04
46.
17
198-0
0.12467E
07
38.06
0i46f919E
04
0.14441 E-02
0.637E-04
46.
18
200.6
0.12635E
07
28.06
0*47160E
04
0.14194E-02
0.632E-04
46.
19
203.2
0. 12802E
07
38.04
0i47397E
04
0.14077E-02
0.614E-04
46.
20
205.8
0.12970E
07
38.13
01476356
04
0.14197E-02
0.622E-04
46,
21
208.5
0.13138E
07
38. 13
0.47869E
04
0.137C3E-02
0.609 E-04
46 •
22
211.1
0.13 30 6E
□ 7
33.10
0^481026
04
0.14045E-02
0.628E-04
46.
23
213.7
0.13473E
07
33.08
Ci48336E
04
0. 1375SE-02
0.615E-04
46.
24
216.3
0. 13642E
07
38.19
01485676
04
0.138136-02
0.632E-04
46.
25
218.9
0. 13810E
07
38.13
0 14 879 7 E
04
0 .135766-02
0.619E-04
46.
26
221.6
0. 139.7 8E
07
37.94
C;49031E
04
0.14298E-02
0.6586-04
46.
27
224.2
0.14146E
07
37.28
0149270E
04
0.1A132E-02
0.602E-04
46.
28
226.8
0.14314E
07
38.06
0i49504E
04
0.13786E-02
0.654E-04
46.
29
229.4
0.14481E
07
37.98
C149739E
04
0.14213E-02
0.620E-04
46 •
30
232.0
0.14649E
07
38.21
0149980E
04
0.144 78E-02
0.654E-04
46.
31
234-6
0.14817E
07
28. 23
Ci50220E
04
0.14067E-02
0.636E-04
46.
32
237.3
0.14985E
07
38.04
0150460E
04
0.145356-02
0.645E-04
46.
3 3
239.9
0. 151546
07
30. 02
0150703E
04
0.14369E-02
0.644 E-04
46.
34
242,5
0. 153226
07
37.81
0150945E
04
0.1446AE-02
0.627E-04
46.
35
245.1
0.15489E
07
37.92
0i51187E
04
0.14350E-02
0.669E-04
46 .
36
247,8
0.15657E
07
37- 60
0*51428E
04
0.1A357E-02
0.734E-04
46.
UNCERTAINTY IN REX=lo28£
UNCERTAINTY IN F=0.05296 IN RATIO
159
RUN
092274-1 ♦♦♦
DISCRETE HOLE RIG *«* NAS-3-14336
STANTCN
NUMBER
DATA
1900STEP40 P«0.4
TH*0
P/C*5
***
RUN
092274-2 ♦**
DISCRETE HCLE RIE **♦ NAS-3-14336
STANTCN
NUMBER
DATA
*** 1900STEP40 M»C*4
TH=l
P/D*5
♦**
LINEAR SUPERPOSITION IS APPLIED TO STANTON NUMBER CATA FROM
RUN NUMBERS 0S2274-1 AND C92274-2 TO OBTAIN STANTCN NU-MEER
CATA AT TH=0 AND
TH=l
PLATE
REXCOL
RE 0EL2
STITH*0I
REXHOT
RE 0EL2
5T(TH=1)
FTA
STCR
F-CGL
SHR
1
796 29 2. 6
69.3
0.004258
796377.3
63. C
0.003870
UUU'JU
1.044
0.0000
0,949
0. 7303
2
828861.1
198.6
0.0036E2
828948.9
173.4
0.002908
0.210
7.869
0.0128
0.950
0.01)5
3
861429.3
316.1
0,003532
861520.6
634.4
0.002455
0.305
0.933
0.0127
0.852
0.7121
4
893997.5
428.3
O.C03357
894092.3
1131.7
0.0)2346
0.391
7.955
0.0127
C.743
0.3117
5
926565.7
535.8
O.C02246
926663.9
1547.7
0.001900
0.415
0.976
0.0127
0.709
0.0115
6
959133.9
640.1
0.003156
959235.6
1981.4
0.001695
0*463
0.992
■3.0123
0.649
3. 3U8
7
99170 2, 1
742 .2
0.C03113
991807.3
2420.2
C. 001673
0.463
1.015
0.0125
C.654
0..3103
8
1024 27 0.0
842.3
0.C03036
1024378.0
2809.7
0.001637
0*461
1.322
0.0126
C.653
0.3105
9
1056838.0
939.6
0.002941
1056950.0
3202.7
C. 001556
0*471
1.017
0.0125
0.631
0.3106
10
1089406.0
1035.9
0. C02969
1089522.0
3595.4
0.001444
0 .514
1.352
0.0121
C. 595
0. 7120
11
1121975.0
1131.7
0.CC2918
1122093.0
4032.9
C. 001366
0.532
1.057
0.0126
0.570
0.0105
12
U54 643.0
1223.7
O.C02728
1154665.0
4417. 5
0.001259
0.539
1. 008
0.0125
0.532
0. 0 1 20
13
1179295.0
1291.2
0.C02754
1179420.0
4839.3
0.001386
0.497
1.032
0.591
14
1196067.0
1335.7
0.C02544
1196194.0
4862. *1
C. 001397
0.451
0.962
C.600
15
1212640.0
1377.3
0.002410
1212968.0
4885.5
0.0)1319
7.453
0.919
0.569
16
1229694.0
1417.5
0.002371
1229824.0
4907.7
0.001332
0.438
0.912
0.578
17
1246548.0
1457.0
0.C02339
1246680.0
4933-2
0. )01346
7.425
0.907
C.537
18
1263320.0
1495.7
0.002211
1262454.0
49 5 2. 7
0.001326
0.416
0.3B7
0.53?
19
1280C93.0
1533.2
0.C02196
1280229.0
4974.9
0.001321
0.398
0.364
0.583
20
1296866.0
1570.1
0. C02193
1297003,0
4997.2
C. 001 33 5
0.391
0.869
0.591
21
1313639.0
1606.4
0. C02137
1313778.0
5019.2
0. 001266
0,398
0.853
0.573
22
1230411. J
1642.0
0.C02102
1330552,0
5041.2
0.001328
0.368
0.845
0,594
23
1347184.0
1677.0
0.C02058
1347327.0
5063.2
C.C01301
0. 368
0. 832
0.584
24
1364C38.0
1711 .6
3.C02C73
1364182.0
5085.1
C. 001305
0.370
0.844
0.589
25
L380892.0
1746 .0
0.002022
1381038.0
5LC6.9
0.001285
0. 364
0.828
0.582
26
1397664. 0
1780.2
3.CC2047
1397813,0
5129.1
C. D31362
7 .334
0.843
0.620
27
1414437.0
1315.3
0.C02134
1414587.0
5151.8
0.001334
0.375
0.854
0.610
28
1431210.0
1850.0
0.0020C6
1431361.0
5174. C
0. )01310
7.347
7.836
0.631
29
1447932.0
1884.2
O.C02065
1446136,0
5196.3
0.001351
0.346
0.865
0.622
30
1464755. 0
1918.5
0.002020
1464910.0
5219,3
C.001385
0.314
7.851
C. 640
31
1481528.0
1952.3
0. C02002
1481685.0
5242.2
0.001341
0.330
0.848
0,623 .
32
1498382.0
1985.3
0.C019S8
1498540.0
5265.2
0.001395
0.298
0.846
C.650
23
1515236,0
2019.4
0.CO2009
1515396.0
5288.4
0.001374
0.516
0.859
0.642
34
1532008.0
2052.8
0.001977
1532171.0
5311.6
0.001286
0.298
0.850
0.651
35
1548781,0
2085.9
0.001963
1548945,0
5334. 8
0.0.71377
0.298
J.848
0.648
36
1565554.0
2118.6
O.C01938
1565720.0
5358. C
C.C01381
0.268
0.841
0.652
ST4NTCN NUMSE'^ RATIO BAS E C ON ST*PR**0.4= 0.0295*RFX** (- .2» *( 1 1 X I /i X-XVOJI 9) ** Ir-1, /9. )
STANTCN KUMSER RATIO FOR TH*! IS CCNVERTEO TO COMPARABLE TRANSPIRATION tfALUF
LSUG ALOGll ♦ Bl/B EXPRSSSICA IN THE BLOWN SECTION
LGGB
0,9%9
2. 34N
2.360
2.223
2. 199
2.176
2.048
2.386
2 .086
2.21 e
2.027
2.151
160
RUN 0*50874 VELOCnv PfCFILE
REX
=
0.241C7E 07
REM »
‘t720.
xvn
17.01
C^.
DFL2 »
0.215
CM
UINF
34. 19
M/S
0FL99=
1.914
Lrt
Vise
=
0, 15594F-04
M2/S
DELI “
0.295
CM
PORT
=
9
H
1.369
XL OC
127.76
CP.
CF/2 =
0.1542 lt-02
Y(CM.) Y/OFL UIM/S) U/tlNF
0.025
0.028
0.030
0.033
0.038
0.043
0.051
0.061
0,074
0.089
0. 107
0.127
0. 150
0. 175
0.206
0.241
0.282
0.356
0.411
0.475
0. 546
0.622
0,711
0. 813
0. 927
1.054
1. 181
1.308
1.435
1- 562
1.689
1.616
1.943
2.070
2. 197
0.013
0.015
0.016
0.017
0.020
0.023
0.027
0.032
0.038
0.046
0.056
0.066
0.078
0.092
0.107
0.126
0,147
0.186
0.215
0.248
0.285
0.325
0.372
0.425
0.484
0.551
0.617
0,683
0.750
0.816
0.883
0.949
1.015
1.082
1.148
17.30
17.69
18.12
18.37
18.77
19.18
19,63
20.03
20.43
21.02
21.52
21.97
22.39
23.0 1
23.28
23.96
24.55
25.33
25.87
26.51
27,09
27.72
28.32
29.08
29,80
30.56
30.94
31.96
32.53
33.05
33.37
33.73
34.03
34,14
34.19
0-506
0.517
0.530
C.537
C.549
C.561
0.574
0.586
C.598
0.615
C.629
C.643
C.655
0.673
0.681
C.701
0.718
0.741
0.757
0.775
0.793
0.811
C.828
C.851
0.872
Y +
21.9
24.1
2t> .2
2t>.4
32 .8
37.2
43.7
52.5
63.4
76.5
91 .6
109.3
129.0
150.9
177.1
207.8
242 .7
306 .2
354.3
408.9
47Q.2
536.8
612 .3
699.3
798.2
U +
12,88
13 • 1 8
13. t9
13.00
13.98
14.28
14.62
14.92
15.22
1 5 .oc
16.03
16.37
16.68
17.14
17.34
17.35
13.29
16.37
19.2 7
19. 75
20,13
20. 64
21.09
21.66
22.20
22.76
23.05
23.30
24. 2j
24.62
2‘t.86
25.12
2 5,34
25.43
26.47
0.894
0,905
0.935
0.951
0.967
C.976
0.986
0.995
0.999
L.OOO
907.5
1016.9
1126.2
1235.6
1344.9
1454.3
1563.6
1672 .9
1732
1691.6
I9I
RUN 090874 *** OI.SCR^TE HCLE RIG *** NAS-3-14336
STANTON NUMBER DATA
TACB =
= 26.38
DEG C
U INF
=
34. 25 M/S
TINF= 25.86
DEG C
FHQ=
1.169
KG/M3
Vise
= 0.15
62 0E-04 M2/S
XVO= 17.8
CM
CP =
1014.
J/KGK
PR =
0*717
***
47C0STEPFP P/D=5
PLATE
X
REX
TO
REE NTH
STANTON NC
DST
DREEN
STITHEOI
rati;
1
127.8
0.24108E
07
35.64
0il6943E
03
0.304246-02
0.557E-04
3.
0.274 24E-02
1.109
2
132.8
0. 25 222E
07
35. 64
0*48 866E
03
3.26901E-02
0.5196-04
5.
0.24169E-02
1.113
*3
137.9
0.26335E
07
35.64
C;78162E
03
0.25706E-02
0.506E-C4
7.
0.22743E-02
1-130
4
143.0
C.27449E
07
35.66
0il06Q8E
04
0.24422E-02
0.492E-04
8.
0.21823E-02
1.119
5
148.1
0. 23563E
07
25. 66
0il3298E
04
0.2383CE-C2
0.487E-04
9.
0.21143E-02
1.129
6
153.2
0.29677E
07
35.64
0*159316
04
0.22413E-02
0. 4836-04
10.
0.20602E-02
1.136
7
158.2
0.30791E
07
25.64
Cil8510£
04
0.22891E-02
0.478E-04
10.
0.20153E-02
1.136
8
163.3
0.319O4E
07
i35.66
0.21024E
04
0.22253E- 02
0.4715-04
11.
0.19769E-02
1.126
9
168.4
0.33018E
07
25. 64
C;23482E
04
0.218 75 6-02
0.4686-04
12.
0.19434E-02
1.126
10
173.5
0.34 13 2E
07
25. 64
0i25892E
04
0.214136-02
0. 4646-04
12.
0.19135E-02
1.119
11
173.6
0.35246E
07
25.64
Q128259E
04
0.21091E-02
0.46 IE -04
13.
0.18867E-02
1.118
12
1 E3.6
0.35359E
07
25.6 2
0*30581E
04
0.20607E-02
0.4575-04
13.
3. 18623E-02
1.1 07
13
187.5
0.37206E
07
35.-26
Oi32279E
04
0.191 706 -02
0.573E-04
14.
0.18451E-02
1.0 39
14
190.1
0. 37730E
07
25. 1C
0*333856
04
0. 19321E-02
0.684E-04
14.
0.18341E-02
1.053
15
192.7
3.38353E
07
25-45
C*34490E
04
0.191 785-02
0.687E-04
14.
0.I8234E-02
1.052
16
195.4
0.339296
07
35.43
C.35587F
04
0.190065-02
0.6746-04
15.
0.18132E-02
1.048
17
198.0
0.39506E
07
25.43
0436678E
04
0.19004E-02
0.675E-04
15.
0.18033E-02
1.054
18
200.6
C. 400796
07
25.41
0.37768E
04
0.189665-02
0.6746-04
15.
0.17938E-02
1.057
19
203.2
0.40 653E
07
25.29
0*38846E
04
0. 185626-02
0.6 56 6-04
16 .
0.17847E-02
1.040
2C
205-8
0.41227E
07
25.47
0.39918E
04
0. 187855-02
0. 6676-04
16.
0.17758E-02
1.058
21
208.5
0. 418006
07
35.41
0i40987E
04
0.184246-02
0.651E-04
16.
0.17672E-02
1.043
22
211.1
0.42374E
07
35-49
C.42044E
04
O.l 63986-02
0.658E-04
16.
0.17589E-02
1.046
22
213.7
0.42947E
07
25.41
0.43091C
04
0.18075E-02
0.641E-04
16.
0.175096-02
1.032
24
216.3
0.43 52 4E
07
25. 52
0.441 3 9E
04
0.184C4E-02
0.660E-04
17.
0.17430E-02
1.056
25
218.9
0.44100E
07
25.45
01451966
04
0.18424E-C2
0.6556-04
17.
0.17354E-02
1.062
26
221.6
0-44674E
07
35.41
0146248E
04
0. 18212E-02
0.6786-04
17.
0, 17280 E-0 2
1.054
27
224.2
0.45247E
07
24. 19
Ol47268E
04
3.17317E-02
J.594E-04
17.
0.17208E-02
1.006
28
226,8
0.45 821E
07
25.25
C.482 94E
04
0. 1E412E-02
0.6a6£-04
18.
0.17138E-02
1.074
29
229.4
0.46395E
07
25. 30
0149329E
04
0.17616E-02
0. 6216-04
16.
0.17070E-02
1.032
30
232.0
0.46 9.6 8E
07
25. 7C
C150360E
04
0.183125-02
0.6606-04
16.
0.170 03 E-02
1.077
31
234.6
0.47542E
07
25.68
0.51401E
04
0. 179196-02
0.6406-C4
18.
0.16939E-02
1.058
32
237.3
0.48118E
07
25.51
0152422E
04
0.17647E-02
0.628E-04
18.
0.168 75 E-02
1.046
33
239.9
0.48695E
07
25.51
0153438E
04
0 .177296-02
0.6385-04
19.
0.16813E-02
1.054
34
242.5
0.49268E
07
25.20
Q154451E
04
0.17569E-02
0.617E-04
19.
0.16753E-02
1.049
35
245.1
0.49842E
07
35.49
01554656
04
0.177355-02
0.6476-04
19.
0.166946-02
1.062
36
247.8
0.50415E
07
25.31
0.56479E
04
0.175926-02
0.674E-04
19.
0.16636E-02
1.057
PUN 091474 *** OISCRETE HCLE RIG *** NAS-3-14336
STANTON number DATA
TACO*
26.19
DEG C
UINF
=
34. lA M/5
TINF= 25.67
CFG C
RHO=
1.171
KG/M3
VI SC
= 0.15579F-04 M2/S
XVC= 17.8
CM
CP=
1015.
J/KGK
PR^
Oi717
***
47 00 STEP 40 H*C
1.4
TH*0
F/D*5
PLATE
X
REX
TO
REENTH
STANTCN NC
DST
0R66N
M
F
T2
THETA
on
1
127.8
0.24111E
07
35.01
0.170 80E
03
0- 306656-02
0.5876-04
3.
2
132.8
0. 2522 5E
07
34. 99
C 148 8376
03
0.263536-02
0.5396-04
24.
0.40
0.0128
25189
0.023
0.033
3
137.9
0.26339E
07
35.03
Oi80813E
03
0. 25062E-02
0.5236-04
41 .
0.39
0.0127
26.03
0.038
0.033
4
143.0
0.27453E
07
25.01
C411367E
04
1.242446-02
0.5156-04
53.
0.39
0.0128
26104
0.039
0.033
5
143. 1
0-2856 7E
0 7
34.99
0il4597E
04
0.238216-02
0.512E-C4
63.
0. 39
0.0127
26104
0.039
0.033
6
153.2
0. 29681C
07
35. Cl
a*17773E
04
0.232C7E-02
0.5048-04
71.
7.39
0.0128
26104
0.039
0.033
7
158.2
0.30795E
07
35.03
0i209L9E
04
0. 22222E-02
0. 5046-04
79.
0.39
0.0128
26119
0.055
0.033
8
163.3
0.319C8E
07
35.01
0.24287E
04
0.231216-02
0.5046-04
86.
0.40
0.0128
26117
0.054
0.033
9
163.4
0. 33022E
07
35. Ci
0427604E
04
0. 227366- C2
0.5006-04
92.
0.40
0.0129
26117
0.053
0.033
10
173.5
0.24136F
07
35.01
0.30912E
04
0. 228626-02
0.5016-04
98.
0.39
0-0127
26114
0.050
0.033
11
178.6
0.35250E
07
25.03
01341476
04
0.22454E-02
0.4966-04
103.
0.39
0.0128
26118
0.055
0.033
12
183.6
0.363646
07
35.01
0*37400E
04
0.220156-02
0.4926-04
109.
0.40
0.0128
26,17
0.053
0.033
13
167.5
0. 37211E
07
34.40
C140008E
04
0.217066-02
0.7596-04
111.
14
190.1
0.37784E
07
34. 20
0.412396
04
0.21156E-C2
0.7576-04
111.
15
192.7
0-58358E
07
34.67
Q 1424426
04
J. 207346-02
0.7486-04
111.
16
195.4
0.38935E
07
24.70
0.43 61 76
04
0.201906-02
0-722C-04
Ill .
17
198.0
0.39511E
07
24.76
0.44768E
04
0,198886-02
0.7126-04
111.
18
200.6
0.4J085E
07
24. 78
C.45899E
04
0. 194966- C2
0. 6986-04
111.
19
203.2
0.40653E
07
24.60
0146999E
04
0. 18807E-02
0.670E-04
112.
20
20 5-8
0.4123 26
07
34. 91
C148C81E
04
0.18860E-02
0.674E-04
112 .
21
208.5
0.41806E
07
34.69
0.491466
04
0.182306-02
0. 6506-04
112.
22
211-1
0.42379E
07
34. 97
C.5Q189E
04
O.101O5E-O2
0.6526-04
112.
23
213.7
0.42933E
07
24.93
0*512176
04
0.17673E- 02
0. 6326-04
112.
24
216.3
0.43530E
07
25. C9
C*522366
04
0.17826E-02
0.646 6-04
112.
25
218.9
0.441O6E
07
35. Cl
Q.53260E
04
0, 178266-02
C.640E-04
112.
26
221.6
0.446806
07
34.93
0.54 2 79E
04
0.176416-02
0.6626-04
112 .
27
224. 2
0.45253=
07
33.77
C* 55 2746
04
0.170196-02
0.5 89 6-04
112.
26
226.8
0.45827E
07
24.93
0i56271E
04
0.17701E-02
0.667E-C4
112.
29
229.4
0.46401E
07
34. 68
Ci57270e
04
0.170 836-02
0.607 E-04
112 .
30
232.0
0.46974E
07
35.26
0i58266E
04
0 .17592F-02
0.639E-C4
112.
31
234.6
0.47 5406
07
25. 24
Ci592676
04
0.172706-02
0.621E-04
112.
32
237.3
0.481246
07
35.09
01602516
04
0.16989E-02
0.6116-04
112.
32
239-9
0.487fllE
07
35. C3
0161235E
04
0.172736-02
0.6266-04
112.
34
242.5
0-49275E
07
34.74
0.62222E
04
0. 171UE-02
0. 6076-04
112.
35
245.1
C.4984 8E
07
24-99
0.63 2096
04
0.172426-02
0. 6356-04
112.
36
247.3
0.50422E
07
24. 60
C164192E
04
0.1699 8E-02
0.662 E-04
112.
uncertainty in REX=556S6. UNCERTAINTY IN F = 0. 05002 IN RATIO
BUN 09167A v*«r CIECBErE HCLE BIG *** NAS-3-14336 STANTON NLWBE^ DATA
TAD6*=
24.41
DEG C
U INF
33.83 M/S
TINF= 23.91
DEG C
RHC=
1. 176
KG/M 3
V ISC
= 0-15411E-04 M2/S
XVQ= 17.8
CM
CP =
1015.
J/KGK
Pft=
0*717
*■¥*
4700STEP40 M=:
). 4
7H=1
P/D»5 ***
PLATE
>
BEX
TO
BEE NTH
STANTCN NO
DST
DREEN
H
F
T2
THETA
OTH
1
127.8
0.2413 7E
07
36. 71
0116627E
03
0.29820E-02
0.420 E-04
2 .
2
132-8
0-25252E
07
36-71
0*46 104E
03
0.23048E-02
0.365E-04
38.
0.37
0.0120
36 A 74
1.003
0.024
2
137.9
0.26 367E
0.7
36. 71
Ci2D262E
04
0.17966E-02
0.329E-04
65.
0.37
0.0119
36 A 67
0.997
0.024
4
143.0
0.27482E
07
36.71
0;35331E
04
0.14853E-02
0.310E-04
83.
0.37
0.0120
36 A 80
1-007
0.024
5
148.1
0.28598E
07
36.69
015037 8E
04
0.13982E-02
0.305E-04
99.
0.38
0.0123
36A74
1.004
0.024
6
153.2
0.29713E
07
36. 69
C*65665E
04
0.1236DE-02
0.302E-04
113.
0.38
0.0123
36A39
0.977
0.024
7
158.2
0.30828E
07
36.71
01805356
04
0.13005E-02
0.300E-04
124.
0.37
0.0120
36A43
0.978
0.024
8
163.3
0.31942E
07
36. 67
0195104E
04
0.12894E-C2
0.300E-04
135.
0.38
0-0121
36165
0.998
0.024
9
168.4
0.33058E
07
36.69
0ill002E
05
0.12055F.-02
0.295E-C4
145.
0.38
0.0122
36.43
0.980
0.024
IJ
173.5
0. 34173E
07
36.67
0il2465E
05
0.119376-02
0.295E-04
154.
0.38
0.0122
36112
0.957
0.024
11
178.6
0-35283E
07
36.67
. 0*13903E
05
0.11557E-02
0.293E-04
163.
0.38
0.0122
35h77
0.930
0.024
12
183.6
0.364G4E
07
36. 71
0-15294E
05
0.1U03E-02
0.290 E-04
170.
0.38
0.0124
35113
0.877
0.024
13
187.5
0.37251E
07
36.52
0U6599E
05
O.llOeOE-02
0.387E-04
174.
14
lSO-1
0.37825E
07
36. 31
0H6664E
05
0.11581E-02
0.404E-04
174.
15
192.7
0.38400E
07
36.59
0*16731E
05
0. 11750E-C2
0.416E-04
174.
16
195.4
0.38 97 7E
07
36.61
0116798E
05
0.11589E-02
0.406E-04
174.
17
198.0
0.39554E
07
36. 61
0.16865E
05
0.11606E-C2
0.407 E-04
174.
IE
200.6
0.40128F
07
36.57
01169316
05
0.1159 8E-02
0.407E-04
174.
19
20 3.2
0.40 7 02E
07
36. 53
C116997E
05
0.11348E-02
0.395 E-04
174.
•20
205.8
0-41277E
07
36.61
0117063E
05
0.11549E-02
0.404E-04
174.
21
208-5
C-41851E
07
56.59
01171286
05
0.11183E-02
0.392E-04
174.
22
211.1
0.42425E
07
36. 61
0;17193E
05
0.1134 8E-02
0.401F-04
174,
23
213.7
O.43O0OE
07
36.57
Qil7258E
05
0.11107E-02
0.389E-04
174.
24
216.3
0.43577E
07
36,71
0*173226
05
0, 113486-02
0.4 04E-04
174.
25
218.9
0.44154E
07
36.63
0il7388E
05
0.11444E-02
0.403E-04
174.
26
221.6
0.44728E
07
36. 52
C117453E
05
0.113 7-9E-C2
0.41 9 E-04
174.
27
224.2
0.453026
07
25.45
CU7516E
05
0.104 HE- 02
0.347E-04
174.
23
226.8
0.45677E
07
36. 50
0117579E
05
0.11477E-02
0.425 E-04
174.
29
229-4
0.4645 IE
07
36.40
0117644E
05
0.11255F-02
0.390E-04
174.
30
232.0
C.47025E
07
36.74
Q117711E
05
0.H812E-02
0.421E-04
174.
31
234.6
0.47599E
07
36.72
0117778E
05
0.11607E-02
0.410E-04
174.
32
237.3
0.48 1.7 7E
07
36.52
01178456
05
0.11570E-02
0.406 E-04
174.
33
239.9
0.48754E
07
36.46
0H7912E
05
0. 117676-02
0.417E-04
174.
34
242.5
0.49328E
07
26- 17
0117979E
05
0.11624E-02
0.401 E-04
174.
35
245.1
0.499026
0 7
36.38
0*18047E
05
0.11893E-02
0.428E-04
174.
36
247.8
0.50477E
0 7
36.17
0118115E
05
0.11733E-02
0,449 E-04
174-
CNCERTfINTY IN REX=55757
UNCERTAINTY IN F=0.C50C2 IN RATIO
t?9I
FUN
C91474 DISCRETE HCLc RIG +♦* NAS-3- 14336
STANTCN NUMBER
DATA
V** 4T00STEP40 M = 0.4
TH=C p/n=5 ♦**
PUN
091674 DISCRETE HCLE RIG *** NAS-3-14336
STANTON NUMBER
DATA
»** 4700STEP40 M=0.4
TH = 1 P/C=5
LINEAR SUPERPOSITION 15 AFPLIEC STANTON NUMBER CATA FPC^
PUN NUMBERS D91474 AND C91674 TO OBTAIN STANTCN NUMBER CATA AT TH=0 AND
TH = 1
PL AT E
REXCOL
RE DEL2
ST( TH=0)
REXHOT
RE DEL 2
ST(7H=1)
ETA
STEP
F-COL
STHR
F-hOT
L33B
1
2411 C97. 0
170.3
0.002067
2413706.0
166. 2
0.072982
UUUUU
1.008
0.0000
0.930
0. 0000
0.933
2
2522490.0
438.3
O.C02643
2525219.0
461. 1
C. 002306
0. 128
0,800
0.0128
0.955
0.0120
2.716
3
2633883. C
776 . 9
U. 002529
2636732.0
2022.5
C. 001797
0*290
0.857
0.0127
0- 791
0.0119
2.579
2145276.0
1054.3
0. C0Z462
2748246. 0
3533.3
0.001467
0 .396
0.899
0.0128
0.632
0.0120
2.492
5
2856669. 0
1326 .9
0.C02422
2859759.0
5028.9
0.001404
0*420
0.935
0.0127
0.665
0.0123
2.554
6
2 968C6 2. 0
1593.3
0. CC2361
2971272.0
6551.4
C. 001326
0.438
0.952
0.0128
0.644
0.0123
2.564
7
3079455.0
1857 .0
0.C02374
3C82786.0
8068.0
,9Tgoi27^,,
0.463
0. 993
0.0128
0.634
0.0120
2.548
8
3 19 0841. 0
212L.4
J. 002372
3194299.0
9551.6
10.0012771
0.462
1.024
0.0128
0.646
0.0121
2.613
9
3302240, 0
2383 .5
0.C02335
3305812.0
11043.6
C .001193
0*489
1.036
0.0129
C.614
0.0122
2.594
13
3413633. 3
2644.3
J. 002343
3417326.0
12532.1
0.0)1156
015)8
1.067
0.0127
0.604
0.0122
2.613
11
3525G26.0
2 903 . 7
0.002310
3528839,0
14022.7
0. 001086
0.530
1.073
0. 0128
0.576
0.0122
2.585
12
3636419. 0
3158.3
0. C02271
3640352.0
15499.2
0.000986
7.566
1.076
0.0128
C.530
0.0124
2.552
13
3721C78.0
3349 .5
0.002238
37251 03,0
16963. 2
C. 000987
0.559
1.076
0.535
14
3778445. 0
3 4 76 .3
0.002176
3782532.0
17021.7
0.001049
0.518
1.055
0.572
15
3035012. 0
3600.0
0. CC2130
3839961.0
170E2.7
C.OOl C73
0.497
1.042
0.589
16
3893457. 0
37 20 .7
0. C02C74
3897669.0
17144. 0
0.001061
0.4B8
1.023
0.586
17
395 1133. 0
2838.9
3. C02341
3955377.0
172C5.2
0.001066
0 *478
1.015
0.592
18
400347 0.0
39 54 .9
O.C02000
4012807 .0
17266.6
C. 001070
0.465
1.002
0.597
19
4065838.0
4067.7
3.C01928
4070236.0
17327.5
C.C0105 0
0.455
0.973
0.589
20
4123205.0
4178.6
0.001932
4127665.0
173 80.5
0.001071
0*445
0.982
0.604
21
4180573. 0
4287 . 7
0. C0i868
4185J95.0
17449.1
0.001038
0*444
0,956
0.588
22
4237940.0
4394.6
0.001853
4242525.0
17509.4
C.00105E
0.429
0.955
0.602
23
4Z953C8. 0
4499.7
0.001809
4299954.0
17569.6
0.001036
0*427
0,938
0.592
24
4352953.0
4604.1
0. C01824
4357662.0
17629.9
0.001061
0*418
0.952
0.609
25
441C599. 0
4708. 8
0.C01823
4415370.0
17691,2
0.001072
0*412
0.957
0.618
26
4467966.0
4812 .9
0. C01804
4472799.0
17752.6
C. 001066
0*409
0.953
0.618
27
4525333.0
4914 . 8
0.001744
4530229.0
17811.1
0.000966
0.446
0.927
0.562
28
4582700.0
5016 .9
J.C01810
4567658.0
17869.8
0.001077
0.405
0.967
0.629
29
4640C69.0
5118.9
0.00 1745
4645088.0
1793 1.2
0.001059
0.393
0.938
0.621
3J
4697436. J
5220.6
0.C01796
4702517.0
17993. 7
0.001115
01379
0.970
0.656
31
4754803.0
5322.3
0.001763
4759947.0
18057.3
C. 001096
0*378
0.957
0.648
32
4812448. 0
5423 .2
0.C01733
4817654.0
18120.3
0.001095
0.368
0.946
0. 649
33
4870094.0
5523.6
0. C01762
4675363.0
1 8193.8
0.001114
0*366
0.967
0.663
34
4927462. 0
5624.4
0.001746
4932792.0
18247.4
0.001100
0*370
0.962
0.657
35
4904829. 0
5725.0
0 . 00 n 5 8
4990221.0
16311. 5
0.001128
01358
0-974
0.676
36
5042196. 0
5825 .3
0. 001733
5047650.0
1 £3 75.9
C. 001113
0-358
0.964
0.670
STANTON NUMBtR RATIO 3ASEO CN ST + P P**0«4=0 .029 5*REX** (- .2 ) ■♦ ( 1 (X I / ( X-XVD )» **0 .9 »*♦(- 1 . /9. )
STANTCN NUMBER RATIO FOR TH*1 IS CCNVERTED TO COMPARABLE TRANSPIRATION VALUE
USING ALOGd * B)/B EXPRESSION IN THE BLOWN SECTION
RUN 102274 VELOCITY AND TEMPERATURE PROFILES
REX =
0.15100E 06
REH
=
515.
REH
448.
xvc =
108.36 Cf*
. DELZ
s
0.066
CM. 0EH2
0.058 CM.
UINF ^
11.83 M/S DEL99=
0.476
CM. DELT99 *
0,456 CM.
Vise =
0.15200E-04 N2/S DELI
=
0.130
CM. UINF
11.
84 M/S
PORT =
19
H
=
1.959
Vise
* 0.
15238E-
04 M2/S
XLCC =
127.76 CN
. CF/2
= 0.
17374E-02
TINF
21.
54 DEG C
TPLATE -
38.
29 DEG C
Y( CM. )
Y/OEL
U(M/S)
U/UINF
v +
U +
YICM.) TIOEG C)
TBAR
TBAR
0.025
0.053
4,14
C.350
8.2
8.41
0.0165
35.44
0.171
0.829
0.02 8
0.059
4.36
0.369
9.1
8.85
0.0190
34.66
0.217
0,783
0.030
0.064
4.40
0.372
9.9
8,93
0.0216
33,76
0,271
0.729
0.033
0.069
4.5 1
0.382
10.7
9.15
0.0241
33.35
0.295
0.705
0.038
0,080
4.7 1
C.398
12.4
9.56
0.0292
32.68
0.336
0.664
0.043
0.091
4.86
0.411
14.0
9.86
0.0343
32.09
0.371
0.629
0.051
0.107
5.09
C.430
It. 5
10.32
0. 0394
31.61
0.400
0.600
0.058
0.123
5.38
G.45 5
19.0
10.91
0.0444
31.26
0.421
0.579
0. 069
0.144
5,55
0.469
22.2
11.25
0.0521
30.81
0.448
0.552
0.081
0.171
5.91
0.500
26.4
11.96
0.0597
30.49
0.467
0.533
0.094
0. 197
6.25
C.528
30.5
12.67
0. 0698
29.97
0.498
0.502
0. 109
0.229
6.66
0.563
35.4
13.51
0.0825
29.54
0.524
0.476
0. 127
0.267
6.98
0.590
41.2
14.16
0.0952
28.93
0.560
0,440
0. 147
0.309
7.38
0.624
47.8
14.97
0.1105
28.48
0.588
0.412
0. 168
0.352
7,91
0.669
54,4
16.05
0.L283
27,78
0.629
0.371
0. 191
0.400
8.51
C.720
61.3
17.27
0. I486
26.95
0.679
0,321
0.213
0.448
8.99
0.760
69.2
18.22
0.1714
26.31
0.717
0.283
0.236
0.496
9.40
0.795
76.6
19,06
0.1994
25.38
0,774
0.226
0.262
0.550
9.88
0.835
84.9
20.03
0.2248
24,58
0.821
0.179
0.287
0.603
10,26
0.867
93, i
20.81
0.2502
23.97
0.858
0.142
0.312
0.656
10.60
0.896
101.3
21.49
0.2756
23.39
0.893
0.107
0.338
0.710
10.92
0.923
109.6
22.15
0.3010
22.96
0,919
0.081
0.376
0.790
11.26
0.952
121.9
22.84
0.3264
22.61
0.940
0,06 0
0.414
0.870
11.4?
0.970
134.3
23.26
0 .3645
22.22
0.962
0.038
0.452
0.950
11.63
0.984
146.7
23.60
0.4026
21-96
0.S78
0.022
0.490
1.030
11. 75
0.993
159.0
23.83
0.4407
21.80
0.968
0.012
0.528
1.110
11.80
0.997
171.4
23.93
0.4788
21.71
0.993
0.007
0. 566
1.190
11.83
l.OOO
183.7
23.99
0.5169
21.64
0.998
0.002
0.555
21.61
0.999
0.001
0,593
21.60
1.000
0.000
PUN 102274 +’<■* OISCRETE HOLE RIG ♦>«* NAS-3-14336
STANTCN NUMBER DATA
TACe-
21 .AC
DcG C
U INF
11.74 M/S
TINF= 21.33
OEG C
RHO =
1 . lee
KG/ M3
V ISC
= 0.15218E-04 P2/S
XVC= 108.4
CM
CP =
1)13.
J/KGK
PR =
0W17
52UHSLFP P/D=
= 5
FLATi:
X
RL X
rn
RSENTH
STANTCN NO
DST
DPEEN
SKTHEOI
RATIO
1
127,3
3. 1497 3G
0 6
3 3.10
3*43 8996
02
0 .2762 86-02
0.689E-04
20.
0. 310936-02
0. 8 89
2
132 .3
0.1Q892E
0 6
33.03
0 ;5532 7E
03
0.3C687E-02
0.717E-04
20.
0. 296816-02
1.034
137.9
0. 228121;
06
26, C8
U*67220L-
03
0.30001E-02
0.711 E-04
20.
0.28582E-02
1.0 50
A
1A3.0
0.2o73lE
0 6
38. C8
0.788256
03
0,292146-02
0.703E-04
20.
0.27690E-02
1.055
c
1A8.1
Q.30651C
06
33. 10
0.901451
03
0.285466-02
0.6976-04
20.
0.26943E-02
1.060
6
153,2
0. 34570C
06
33.11
C*IQ1C8L
04
0,272676-02
0.685E-04
20.
0.263026-02
1.037
7
158.2
0. 384906
06
33. ce
0.111786
04
0. 27297E-02
0.6S7E- C4
20.
0.25743E-02
1.060
8
163.3
3.42 4C9E
Go
38. ce
C. 122286
04
0.263176-02
0.678E-04
20.
0.25249E-02
1.043
9
16 8 .4
0. A63296
Ob
38. 10
0.132506
04
0 .2SB12E-02
0.673E-04
20.
0.248066-02
1.041
IJ
173.5
0.5 J248E
0 6
38. 11
0.142456
04
0.24944c- 02
0.6666-04
20,
0. 244066-02
1.022
11
173.6
0.54168E
06
38 .11
0.152196
04
0.24739E-02
0.6646- 04
21.
0.240436-02
1.029
12
183,6
G. 58C87E
06
3 3. C 8
0.161816
04
0.24375E-02
0.662 E-04
21.
0.23709E-02
1.028
13
187.5
0.6L066E
0 6
26.40
0.168 726
04
0, 2 1056E-02
0.726E-04
21.
0. 234736-02
0.897
JA
190.1
C.63 C65t
06
3d. 08
0*173006
04
0 .21353E-02
O.BOlE-04
21.
0.233216-02
0.916
15
192.7
0 .65103E
06
26.31
0*177306
04
0.211 77G-C2
0.810E-04
21 .
0-231746-02
0.9 14
It
195.4
0.67132E
06
36.31
0*181566
04
0.210 26 c- 02
0,796 E-04
21.
0. 230336-02
0.913
17
198.0
0.691o0E
06
36. 23
C. 185816
04
0.210C46-02
0.799 E-04
21 .
0. 228966-02
0.917
18
200.6
0.71178E
06
26.27
0*190056
04
O.ZlOOOE-02
0.798E-04
21.
0. 227656-02
0.922
19
20 3.2
0.73197E
0 6
2 6 . 2 1
C.19428E
04
0.2C7756-C2
0.779E-04
21.
0. 226386-02
0.918
20
20 5.8
0.75216E
06
36.31
0.19e49E
04
0.20934E-02
0.7936-C4
21.
0. 225156-02
0.930
21
208.5
0. 77234E
0 6
36. 23
0.20270E
04
0.2071 lE-02
3.7806-04
21.
0. 223966-02
0.9 25
22
211.1
0. 79253E
05
35.27
0*206906
04
0. 208386-02
0.797E-04
21 .
0.22281E-02
0.935
22
213.7
C. 812716
06
36. 23
0*211Q6£
04
0. 203906-02
0.7766-04
21.
0.221696-02
0,920
2A
216.3
0. 833006
06
36.33
0*21520E
04
0.205046-02
0.7976-04
21.
0.220 606-02
0.929
25
213 .9
0. E5328E
06
36. 15
Ci21933E
04
0.2Q422E-02
0.780E-04
21.
0.21954E-02
0.930
26
221.6
U.87346F
06
36.06
0;Z2346E
04
0.204A16-02
0. 8236-04
21.
0.21851E-02
0.935
27
224.2
0. 893656
06
35.01
Ci2276lb
04
0.206 066-02
0.733E-04
21.
0.21752E-02
0.947
28
226.8
0.91384E
06
36. 12
0*23174F
04
0. 202806-02
0,8266-04
21.
0.21655E-02
0.937
29
229,4
0. 934026
06
26. CA
0i235906
04
0.208616-02
0.776 E-04
21.
0.21560E-02
0*9 68
30
232.0
0.954216
06
36-A8
C-24006E
04
0. 2031 5E- 02
C.799E-04
21.
0.21468E-02
0.946
21
234.6
0.97439C
06
36. A2
0.244176
04
0.20396E-02
0.780E-04
21.
0.21379E-02
0.954
32
237.3
0. 99466E
06
36. 24
C*24025E
04
0. 199496-02
0.770E-04
21 .
0.21291E-02
0,937
33
239.9
0.101506
07
26.27
0*252326.
04
0.20320E-02
0.7826-04
21.
0.21205E-02
0.958
3A
242.5
0.10351E
07
36-C4
0i25d38r
C4
0. 198416-02
0.746E-04
21.
0.21122E-02
0.9 39
35
245.1
0.10553E
07
26.21
0.260396
OA
0. 199106-02
0.7946-04
21.
0.21040E-02
0.946
36
247.8
0.10755E
07
*5. 89
C *264366
04
0.19315E-02
0.850E-04
21.
0.20961E-02
0.921
RUN 103074-1 DISCRETE HCLF RIG NAS-3-14336
STANTON NUMBER CATA
TADB*
20,29
DEG C
U INF =
11.70
M/S
T INF=
20.23
DEG C
RHQ=
1.200
KG/M3
VISC= 0.15041E-04
M2/S
XVG =
108.4
CM
CP»
1011.
J/ KGK
PR-
0*716
*** 520HSL40 HsO.4 TH=0 P/D=5 ***
PLATE X
REX
TO
REE NTH
STANTCN NO
OST
DREEN
M
F
T2
THEfA
DTM
1
127.8
0.15095E
06
36. G6
0*48211E
03
0.29776E-02
0.736E-04
20.
2
132.8
0.19047E
06
36. G8
Ci60465E
03
0.22246E-02
0.759E-04
21.
0.42
0.0137
2U58
0.085
0.019
3
137.9
0.22999E
06
36.08
0.77660E
03
0.31458E-02
0.751E-04
22.
0.41
0.0134
2l;96
0.109
0.019
4
14 3.0
0.26951E
06
36. 13
0i95585E
03
0.29995E-02
0.736E-04
23.
0.41
0.0132
21*89
0.104
0.019
5
148.1
0. 309.02 E
06
36. C8
0.U2S4E
04
0.2980 8E-02
0.736E-04
25.
0.40
0.0131
21; 86
0.103
0.019
6
153.2
0.34 854E
06
36.10
0il2974E
04
0.28816E-02
0.726E-04
26.
0.40
0.0130
21494
0.108
0-019
7
158.2
0.388C6E
06
36. C6
0il4667E
04
0.2E799E-02
0.728E-04
27.
0.42
0.0137
22*06
0.115
0.019
a
163.3
0.42 75 7E
06
36.02
Oil6428E
04
0.286996-02
0.728E-04
28.
0.41
0.0133
21496
0.109
0-019
9
168.4
0.467G9E
06
36. C8
Cil8l27E
04
0.281 83E-02
0.721E-04
29.
0.41
0.0131
22 401
0.112
0.019
10
173.5
0-50661E
06
36. C6
0.19828E
04
0.26561E-02
0.725E-04
30.
0.40
0.0131
22 4 02
0.113
0.019
11
178.6
0.54612E
06
36. 10
a.21528E
04
0.280 13 E-02
0.719E-04
31.
0.40
0,0129
22.07
0.116
0- 019
12
183.6
0.58564E
06
36-08
C.23208E
04
0.27017E-02
0.7116-04
32.
0.40
0.0130
22*06
0.115
0.019
13
187.5
0.61567E
05
34- 17
C124579E
04
0.238 70E-02
0.809 E-04
32.
14
190.1
0.63603E
06
33.85
0*250646
04
0.23756E-02
0.884E-04
32.
15
192.7
0.65638E
06
34. 13
0*255406
04
0.22927E-02
0.875F-04
32.
16
195,4
0.67683E
05
34.17
0.26002E
04
0-2242 7E- 02
0.849 E-04
32.
17
198.0
0.69728E
06
34.21
C.26456E
04
0. 221416-02
0.841E-04
32.
18
200.6
0.71763E
06
34. 21
OJ26901E
04
0.21576E-02
0.824E-04
32.
19
203.2
0.73798E
06
34. 19
0*273356
04
0.210 0 26- 02
0.794E-04
32.
20
205.8
0.75833E
06
34. 27
Ci27765E
04
0.21203E-02
0.8056-04
32.
21
203.5
0.77868E
06
34.27
0.28187E
04
0.2C2C7E-02
0.769E-04
33,
22
211.1
0-799O3E
06
34.40
0.28595E
04
0.19867E-02
0.777E-04
33.
23
213.7
0. 81938E
□ 6
34.32
01289986
04
0. 19671E-02
0.757E-04
33.
24
216.3
0.S3S83E
06
34.44
0*29399E
04
0. 197226-02
0.7 76 E-04
53.
25
218.9
0.8602BE
06
34. 34
C*29796E
04
0.191 6 BE- C2
0.750E-04
33.
26
221 .6
0.88064E
06
34.23
0*301866
04
0.191326-02
0.765E-04
33.
27
224.2
0.9Q099E
06
33. 25
01305816
04
0.19645E-02
0.714E-04
33 .
28
226.8
0. 92134E
06
34.30
0*309756
04
0.1906 86-02
0.790E-04
33.
29
229.4
0.94169E
06
34. 28
C*31367E
04
0.19346E-02
0.7 38 E-04
33.
30
232.0
0.96204E
06
34.63
0*317596
04
0.19121E-02
0.761E-04
33.
21
234.6
C.98239E
06
34.63
0.32145E
04
0.18771E-02
0.737E-04
33.
32
237.3
0.1002 8E
07
24, 53
01325266
04
0.1863 16-02
0.731E-C4
33.
32
239.9
0.10233E
07
34.51
01329046
04
0.18491E-02
0.732E-04
33.
34
242.5
0.10436E
07
34.25
C*33282E
04
0.1E636E-02
0.7126-04
33.
35
245. 1
0, 106406
07
34.40
0.33657E
04
0 .161286-02
C.744F-04
33.
36
247.8
0.10843E
07
34. C7
C*34C216
04
0.1 /657E-02
0.805 E-04
33.
UNCERTAINTY IN REX=197S£- UNCERTAINTY IN F=U. 05145 IN RATIO
RUN 103074-2 *** DISCRETE HOLE RIG ♦** NAS-3- 14336
S^AMTOM NUMBER DATA
TACB =
20.31
DEG C
UINF
=
ia.68 M/S
TUF= 20*25
DEG C
PHO =
1.200
KG/M3
V ISC
= 0.15043E-04 M2/S
XVD= 108.4
CM
CP =
1011.
J/KGK
PR =
01716
**-k
520HSL40 M=C.A
h TH
= 1 P/D
a 5 ♦**
PLATE
X
REX
TO
REENTF
STANTCN NO
DST
DREON
M
F
T2
THETA
DT^
1
127.8
0. 1507 IE
0 6
37.41
0148134E
03
0.28623E-02
0 • 6 8 4 F -0 4
20.
2
132 .8
0.L9O17E
06
37.41
0i59124E
03
0.27090'E-02
0.670E-04
23.
0. 39
0.0126
35140
0.883
O.OLB
3
137.9
0. 22962E
0 6
37.41
Cm283E
04
0. 227442-02
0.635E-04
29.
0.40
0.0129
36U5
0.926
0.018
A
143.0
0.26908E
06
37.45
0U683 2E
04
0. ie7C8=-02
0.605E-04
35.
0.39
0.0125
36116
0.925
0.018
5
148.1
0.3C853F
06
37.43
0.22129fc
04
0.17922E-02
3.601E-04
39.
0.40
0.0130
35*93
0.913
0.018
6
153.2
Q. 3479 8E
06
37.45
C*27492E
04
0.l7142t-02
0. 595E-04
43.
0.41
0.0132
35*79
0.903
0.018
7
158.2
0. 38744E
OS
37.47
C.32877E
04
0.16797E-02
0.593E-04
47.
0, 40
0,0131
35*59
0.891
0.018
Q
163.3
0.426B9E
06
37,45
C*38132E
04
0.16504E-02
0.591F-04
50.
0.38
0.0122
36-29
0-932
0.018
S
163 .4
0.46 63 5E
06
37,43
0,4-3272F
04
0.le210E-C2
0.590E-04
53.
0. 38
0.0121
35163
0-895
0.016
10
173.5
0.50580E
06
37.45
Ci48195E
04
0.15077E-02
0.588 E-04
56.
0.43
0.0138
35111
0.864
0.018
1 1
178.6
0.54525E
06
37.47
0.53530E
04
0.15653E-C2
0.586E-04
59.
0.41
0.0132
34188
0.850
0.018
12
183.6
0.584J1E
06
37.45
C158556E
04
0.15301E-02
0.5 84 E-04
61 .
0.41
0.0134
34172
0.841
0.018
12
187.5
C.6146i9E
06
36. 34
0163457E
04
0.14113E-02
0. 526E-04
63 .
14
190. 1
0.63501E
06
26. C6
Oi63750E
04
0.147C3E-02
0,588 E-04
63.
15
192.7
0.65533E
06
36.31
0-64 046 E
04
0.14428E-02
0.588F-04
63.
U
195.4
0.67535E
06
36.31
C164341E
04
0.14528E-02
0.583E-04
63 .
17
193.0
0-696i6E
06
26.31
C*64637E
04
0 .1A5 7 7F.-02
0.585E-04
63.
18
200.6
0- 71648E
06
36. 31
Ci64930E
04
0.14273E-02
0.578E-04
63.
19
203.2
0.736B0E
06
36. 29
0-65216E
04
0. 13838E-02
0.55BE-04
63.
2C
205.8
0.75712E
06
36.21
0i65506F
04
0, 146339-02
0.574E-04
63.
21
208.5
0.77744E
06
36. 34
C165792E
04
0.I3512E-02
0.552F-C4
63.
22
211.1
C.79776E
.0 6
36.33
0166071E
04
0.12937E-02
0.568E-04
63 .
23
213.7
0.B1808E
06
36. 33
Qi66352E
04
0, 13629E-02
0.555E-04
63.
24
216.3
0. b3849E
06
36 . 48
0466629E
04
0.13584E-02
0.570E-04
63.
25
218.9
0.65891E
06
26.34
0^66904E
04
0.13534E-02
0.558E-U4
63 .
26
221.6
0-87923E
06
26, 19
0J67182E
04
0 .12787E-02
0.5 86E-04
63.
27
224.2
0- 89955fc
06
35. 51
0167458E
04
0.13287E-02
0.521F-04
63.
28
226.8
0.91987E
06
36.31
0167730E
04
0.13505E-02
0.587E-04
63,
29
229.4
C. 94019E
06
36.23
C168008E
04
0,1 37 9 IE- 02
0.551E-04
63.
30
232 .0
0.96 031t
06
36. 50
C468290E
04
0.13928E-02
0.580E-04
63.
31
234.6
C.90C82E
06
36.52
0.68 569E
04
0.13532E-02
0.563F-04
63.
32
237.3
C.10012E
07
36. 23
Cl6884eE
04
0. 13914E-02
0. 5680-04
63 •
33
239.9
0.10217F
07
36. 23
0169130E
04
0.13757E-C2
0.569E-04
63.
34
242.5
0. 1'J420E
07
26. 12
0-69409E
04
0.13668E-02
0,548 E-04
63 .
35
245.1
0. 10623E
07
26.21
0 469686E
04
0. 13633E-02
0.584F-04
63.
26
247.8
C. 1C626E
0 7
25. 94
0169960E
04
0.13265E-02
0.628E-04
63.
UNCERTAINTY IN REX=1 972 7
UNCERTAINTY IN F=0. 05146 IN RATIO
RUN
10307^1 **■* DISCRETE HCLE RIG ♦♦♦ NAS-3-14336
STANTON NUMBER DATA
520HSL4C
Ms C.4
Th=0
P/D = 5 ***
RUN 103074-2 DISCRETE HOLE RIG
*** NAS-3-
-14336
STANTCN NUMBER DATA
520HSL40
H=0.4
II
X
P/D=5
LINEAR SUPERPOSITION IS Af PLIED TO STANTON NUMBER CATA FRCM
PUN NUMBERS 103074-1 AND 103074-2 TO OBTAIN STANTCN NUMBER DATA AT TH*0 AND TH=1
AT6
REXCOL
RE DEL2
ST{TH=0>
REXHOT
PE DEL2
SKTHsIJ
ETA
STCF
F-COL
STH5
P- HDf
LQS3
1
150954, e
482.1
0. C02978
150712.9
481.3
0.00286 2
■JU'JJJ
1.078
0.0000
1.036
0. 0000
1, 03 6
2
190471.8
605.7
O.CO320O
190167.8
58S.7
0.002633
0.197
1.106
0.0137
0.888
0,0126
2.420
3
22S98E. 8
734.8
J. C03251
229621.7
11 81.6
3.0)2171
0.332
1.139
0.9134
G.760
0.0129
2.336
4
269505.8
861,2
0.00 '147
269075.6
1770. 1
0.001768
0.43 8
1. 133
0. 0132
0.63 9
0,0125
2.167
5
309022. 7
985.2
0. C03132
308529.5
2332.5
0.0)1674
0*466
1.164
0.0131
C.622
.0.0 130
2.222
6
348539. 7
1107 .1
0.C03035
347983.4
29CB. 5
C. 001580
0.479
1.155
0.0130
0.601
0.0132
2.250
7
388056. 7
1227.3
O.C03050
387437.3
3491.8
C. J )1522
J.5H
1.186
0.0137
0.592
0.9131
2.249
8
427573.6
1347.6
0. C03041
426891.3
4067.9
0.001516
0 * 50 2
1.206
0.0133
0.601
0.0 122
2.197
9
467090.6
1466.7
0.C02983
466345.1
4609.2
0.001493
0.500
1.2 04
0.0131
0.602
0.0121
2.215
ID
506607.6
1585,7
0. C03042
505799.1
£145.2
O.OD13S8
0 ,544
1.248
0.0131
0.569
0.0133
2.369
11
546 124.6
1 704 . 9
545252.9
£744.4
0.001327
0, 556
1.246
0.0129
0,552
0.0132
2.293
12
585641.6
1021.1
U-C02EE7I
584706.9
6315.4
0.)Jl282
0.556
1.219
0.0130
0,541
0. 0134
2.323
13
615674.6
1904,0
0. 00254 1
614691.9
6382.6
0.001205
0. 52 6
1.084
0.514
14
636025.8
1955.6
0. C02519
635010.6
6907.9
3.D01279
0*492
l.OBl
0.549
15
656377.0
2006 .0
0.C02427
655329.4
6933. 8
C. 001263
0.480
1.049
0.545
16
676E26.8
2054.3
0.002368
675746.6
6959.7
0.001286
0.45 7
1.029
0. 559
17
697276.9
2102.7
0.CC2334
696164.0
6986. C
0.001298
0.444
1.020
0.567
18
717628. 1
2149.6
O..C02273
716402.8
7012.1
0.0 J1273
0.440
1.009
C.569
19
737979.3
2195.3
0.002214
736801.5
7037.6
C. 001232
0.443
0.979
0.545
20
75823C.6
2240.6
0,002224
757120.3
7063.6
0.001224
0 .405
0.989
0.589
21
778682. 1
2284.9
0. CC2127
777439.3
7089.4
C. 001210
0.431
0.951
0.541
22
799033.3
2327.7
0.002080
797758.0
7114.6
C. 001268
0*390
0.935
0.570
23
019284 . 5
2369.9
D. 002063
818076.8
714 3.0
J.OJ1235
0.401
0.932
0.558
24
839834.3
2412 .0
O.C02069
838493.9
7165.1
C.C01228
0,406
0.939
0.551
25
E60284.4
2453.6
0. C02CCa
858911.4
719 J.l
0.0)1234
.0,386
0.916
9.562
26
800635.6
2494.4
0.001998
879230.1
7215.6
C. 001266
0.366
0.915
0.580
27
9CC986.9
2535 .8
■D.C02065
899548.9
7240.6
0.001194
).422
0.9 5J
0.549
28
921338.1
2577.2
0. C0199 5
919867.6
726 5.3
0.001233
0*382
0.922
0,570
29
941689.6
2618.1
0.002023
940186.6
7290.6
C. 001262
0.376
0.939
0. 536
30
962040.8
2659 .0
0.CC1994
96C505.4
7316.5
C. 001283
0*357
0.9 30
0.593
31
982392.0
2699.3
0.001960
980824.1
7342.2
0.001242
0.366
9.910
0.582
32
1002841.0
2739. D
D. C01938
1001241.0
7368.0
0.001292
0.333
0.911
0.607
33
1023291.0
2778.3
0.CO1924
1021656.0
7394.1
C. 001276
0.337
0 . °oa
0.692
34
1043643. D
2817.7
D. 001942
1041977.0
7419.9
0.301262
0.350
0.921
0,598
35
1063994.0
2856.7
0.001884
1062296.0
7445.6
C. 001268
0.327
0.856
0.603
36
1C64345.0
2394.6
0.C01835
1082614.0
7471.1
3.031234
0.328
0.877
0.589
STANTCN NUMBER RATIO BASEL ON ST*PR**0 .4=0 .029 5*P (- . 2 »
STANTON NUMBER RATIO FOR TH=1 IS CONVERTED TO COMPARABLE TRANSPIRATION VALUE
USING ALCGU + 8)/B EXPRESSION IN THE BLOWN SECTION
170
RUN 102 874
CISCRcTE HOLE RIG *** NAS-3- 14336
STANTCN NUMBER DATA
TACE= 21.55 OEG C UINF= 11.76 M/S T INF= 21.49 DEG C
RHC* 1.185 KG/M3 VISC* 0.15252E-04 M2/S XVO= 108.4 CM
CP= 1014. J/KGK PR= 0^717
520HSL75 M»0.75 TH=0 P/C=5
PLATE
X
REX
TO
REE NTH
STANTON NO
DST
DREEN
M
F
T2
THETA
DTH
1
127.8
0. 14957E
06
37. 12
0i52663E
03
0.30046E-02
0.749 E-04
2D.
2
132.8
0.188J3E
06
27. C9
0i65069E
03
0.22323E-02
0.781E-04
22.
0.78
0.0254
21*09
0,026
0.020
•a
137.9
C.22788E
06
37.09
01B1210E
03
0.35951E-02
0.807 E-04
26.
0.79
0.0256
22il4
0.042
0.020
4
143.0
0. 26703E
06
27-11
Ci99426E
02
0.257C9E-02
0.804E-04
30.
0,79
0.0257
22110
0.039
0.020
5
148.1
0. 30619E
06
37. 11
0U1720E
04
0.35069E-02
0.797E-04
33.
0.79
0.0256
22109
0.038
0.020
6
153.2
0.34534E
06
27. C9
0a3457E
04
0.24026E-02
0.788 E-04
36.
0.79
0.0254
22115
0.042
0.02 0
7
158.2
0.33450E
06
37-09
0115215E
04
0. 24224E-02
0.790E-04
39.
0.78
0.0253
22125
0.049
0.020
8
163.3
0.42365E
06
27.09
0a7034E
04
0.341096-02
0.789E-04
41.
0.78
0.0254
22121
0.046
0.020
9
163.4
0.46281E
06
37.07
0.18832E
04
0.34233E-02
0.791E-04
44.
0,79
0,0255
22119
0.045
0.020
10
173,5
0.50L96E
06
37. 11
Oi2 0630E
04
0.34535E-02
0.792 E-04
46.
0.79
0.0255
22119
0.045
0.020
11
178-6
0.54112E
06
27.11
0i22425E
04
0.34421E-02
0.791E-04
48.
0.79
0.0256
22127
0.050
0.020
12
183-6
C.58027E
06
27.12
0i24255E
04
0.33651E-02
0.783E-04
50.
0.79
0.0255
22«28
0.050
0.020
13
187.5
0.610J03E
06
24.78
0i25717E
04
0.25853E-02
0.990E-04
51.
14
190.1
0.63019E
06
34.42
0i26312E
04
0.29097E-02
0.106E-03
51.
15
192.7
0.65036E
06
24.76
0A26fi86r:
04
0.27964E-02
0.105E-03
51.
16
195.4
0.670626
06
24.82
C>k27445E
04
0.27242E-02
0.102E-03
51.
17
198.0
0.69088E
06
54.66
Oi27990E
04
0.26714E-02
O.lOOE-03
51.
18
200.6
0.71105E
06
34. 80
0A28525E
04
0.26266E-02
0.985E-04
51.
19
203.2
0.73121E
06
34. 74
0A29O51E
04
0.25871S-02
0.954E-04
51.
20
205.8
0.75 130E
06
35.01
Oi29562E
04
0.2477fiE-02
0.940E-04
51.
21
208.5
C. 77164c
06
24.89
0*30063E
04
0.24791E-02
0.921E-04
51.
22
211. 1
0-79 17 IE
06
25. C5
OA30556E
04
0,241 C7E-02
0.922E-04
51.
22
213.7
0.81187E
06
35.01
0i31038E
04
0.22607E-02
O.091E-O4
51.
24
216-3
0.83213E
06
35. 14
Oi31512E
04
0.23358E-C2
0.904E-04
51.
25
218.9
0.85240E
06
34.99
0i3l978E
04
0.22854E-02
0.871E-04
51.
26
'221.6
0.67256E
06
24.55
C.32437fc
04
0.22621E-02
0.912E-04
51.
27
224.2
0.89273E
06
33. 92
0A32896E
04
0.22818E- 02
0.815E-04
51.
28
226.8
3.91289E
06
25.05
G*33351E
04
0.22270E-02
0.906 E-04
51.
29
229.4
0.933Q6E
06
35.03
0133600E
04
0.22224E-02
O.B32E-04
51 .
30
232.0
0.95322E
06
25.49
0A34243E
04
0.21672E-02
0.856 E-04
51.
31
234.6
0.9733EE
06
35.45
0A346 79E
04
0.21442E-02
0. 826E-04
51 .
32
23 7.3
0.9936 5E
0 6
35.37
0A35106E
04
0.20922E-02
0.311E-04
51.
33
239.9
0,1J139E
07
25. 25
CA35527E
04
0.2C782e-02
0.812E-04
51 .
34
242.5
0.10341E
07
35.09
0;35946E
04
0.2C716E-02
0.782E-04
51.
35
245.1
0.10542E
07
25. 20
CA36357fc
04
0.2C019E-02
O.013E-O4
51.
36
247. B
0.10744E
07
34.97
0 A36757E
04
0.19567E-02
0.873E-04
51.
UNCERTAINTY IN REX*19577. UNCERTAINTY IN F»0. 05146 IN RATIO
FUN 102974 *** DISCRETE HOLE RIG *** NAS-3- 14236
STANTON NUMBER DATA
TACB=
21.24
DEG C
UINF
=
11.75 M/S
TINF= 21.18
DEG C
RHC =
1 .186
KG/M3
V ISC
» 0.152
54E-04 M2/S
XVO= 10 6.4
CM
CP =
1011.
J/KGK
PR=
0.715
520HSL75 M?0.75 TH=1 P/D = 5
PLATE
X
REX
TO
REF. NTH
STANTON NO
DST
DREEN
M
F
T2
THETA
1
127.8
0.1494 EE
06
38. 15
C*52622E
03
0.29512E-02
0.700 E-04
20 .
2
132.8
0-18861E
06
38. 13
C*63889F
03
0.2E023E-02
0.687E-04
31.
0.74
0.0241
36186
0.925
3
137.9
0.22774E
06
3’3. 13
0.16217E
04
0.2E625E-02
0.693E-04
46.
0-73
0.0238
37^03
0.935
4
143.0
0.26688E
06
3 3.11
0 4255596
04
0.251 82E-C2
0.664E-04
57.
0.74
0.0238
37130
0.952
5
148.1
0. 30601E
06
38.13
0.35770r
04
0.23260E-02
0.648E-04
67.
0.70
0.0227
37114
0.941
6
153.2
0.34514E
06
38. 13
Ci450l2E
04
0.22077E-02
0.639E-04
74.
0.73
0.0238
36183
0.923
7
153.2
0.38427E
06
33. 13
0.54459E
04
0.220 13E- 02
0.639E-04
82.
0.73
0. 0236
36185
0.924
8
163.3
0.42 340E
06
33. 13
C;63830E
04
0.21405E-02
0.634E-04
88.
0.72
0.0233
37*14
0.941
9
168.4
0.46253E
06
38.15
0i73257E
04
0.21097H-02
0.631E-Q4
94.
0.73
0.0237
36174
0.917
IJ
173.5
O.Sn66E
06
38. 33
0*825E5E
04
0.2C745E-02
0.629E-04
100.
0.72
0.0234
36139
0.897
11
178.6
0.54080E
06
38. 15
C.91618E
04
0.20348E-02
0.626E-04
105.
0.72
0.0233
36111
0.879
12
183.6
0.57993E
06
38. 15
0.1OQ41E
05
0.19961E-02
0.623E-04
109.
0.71
0.0231
35144
0.840
13
187.5
0.60967E
06
36. 67
0.10857E
05
0.1E335E-02
0.644E-04
111.
14
190.1
0.62982fc
06
36. 4C
0*10893E
05
0 .17976E-02
0.691E-04
111.
15
192 .7
0.64997E
06
36.72
0il0S29E
05
0. 17263E-02
0.683E-04
111.
16
195.4
0.67C22E
06
26.78
0410964E
05
0.16892E-02
0. 6616-04
111.
17
198.0
0.69047E
0 6
36. £4
Ca0997E
05
0.16454E- 02
0.650E-04
111.
le
200.6
0.71063E
06
36.84
C*11030E
05
0.159 77E-02
0.634E-04
111.
19
20 3.2
0.730763
0 6
36. 66
0411C62E
05
0.15378E-02
0. 6036-04
111.
20
205.6
U.75093E
0 6
37. C3
0411092E
05
0.15012E-02
G. 5996-04
111.
21
208.5
0.77108E
06
37.C5
0411122E
05
0.14372E-02
0.5786-04
111.
22
211.1
0.79124E
06
37.05
C411151E
05
0.14366E-02
0. 5856-04
111.
22
213.7
0.81139E
06
37. C 5
C411179E
05
0.13848E-02
0.5646-04
111.
24
216.3
0-E3ie4E
06
37.22
04112C7E
05
0. 125156-02
0. 572 6-04
111.
25
218.9
0. E5189E
06
37. 12
0U1234E
05
0.13032E-02
0.5476-04
111.
26
221-6
0.87204E
06
26.59
C411260E
05
0.13242E-02
0.5716-04
111.
27
224.2
0.89219E
06
36.36
0ill286E
05
0.12336E-02
0.4996-04
111.
28
22 6.8
0.91235E
06
37. 16
C411311E
05
0.12535E-02
0.5596-04
111.
29
229.4
0.93250E
06
37.12
0ai336E
05
0.12614E-02
0.5186-04
111.
30
232.0
0.95265E
06
37.45
0ai362E
05
0.12432E-02
0.5406-04
111.
31
234.6
0.97281E
06
27.47
Oai386E
05
0.12052E-02
0.5 196-04
111.
22
237.3
0.993Q6E
06
37.35
QilI411E
05
0.12063E-02
0.517E-04
111.
32
239.9
0.10133E
07
27.35
Oill435E
05
0-1186^E-02
0.5146-04
III.
34
242.5
0-13335E
07
27.16
0ai459E
05
0.11673E-02
0.492E-04
111.
35
245.1
0.10536E
07
27.24
041 148 2E
05
0.11515E-02
0.526E-04
111.
36
247.8
0.10738E
07
36-93
C.11505E
05
0.11298E-02
0.559E-04
lU.
INCERTAINTY IN REX=19566. UNCERTAINTY IN’ F=0 .051A6 IN RATIO
DTH
0.018
0.018
0.018
0.018
O.OIB
0.018
0. 018
0.018
0.018
0.018
0.018
PUN 102874 DISCRETE HCLE RIG ♦** NAS-3-142'6 STANTCN NUMBER DATA
»♦* 520HSL75 M=0.15 TH = 0 P/D*5 ♦**
RUN 132974 **•(' DISCRETE HCLE RIG *** NAS->14336 STANTON NUMBER DATA
520HSL75 K»0.75 Th=l P/D=5 *+♦
LINEAR SUPERPOSITICN IS APPLIED TO STANTON NUMBER DATA FROM
RUN NUMBERS 102374 AND 102S74 TO OBTAIN STANTCN NUMBER DATA AT TH=0 AND TH=1
PLATE
REXCOL
RE DEL 2
5T(TH=0I
R.E XH OT
RE DEL2
ST(Th=1»
ETA
STCR
F-COL
STHR
P-HOT
L03B
1
1A9570. 7
5 26 .6
0.003CC5
149481.8
526,3
0.0)2951
UUUUU
1.088
0.0000
1.068
0.0000
1.068
2
183725.4
651 .0
0.003348
186613.1
638,0
0.002758
0. 176
1.127
0.0254
0.928
0.0 241
3.563
3
227880. 0
787.4
0.003623
227744.4
1689.6
0.002805
0.226
1.266
0.0256
Q.981
0.0238
3.693
4
267C34.7
929.2
0. C02616
266875.8
2721.9
0.002452
0*322
1,306
0.0257
6.8B5
0.0238
3.622
5
306189. 3
1069.7
0.003557
306007.2
3745.2
0,002256
0.366
1. 319
0.02 56
0.837
0.0 227
3.501
6
345343. 9
1207 .0
0. C03457
345138.6
471 8.5
0.002117
0*388
1.313
0.0254
0.804
0.0238
3.605
7
384498.6
1342 . 9
0. 003485
384269.9
573 1.0
0.002102
0.397
1.353
0. 02 53
0.816
0.0236
3.654
8
A23652. 3
1479.2
3. C03479
423401.3
6734.1
0.002044
0*413
1.377
0 . 02 54
0.809
0. 0233
3.666
9
462807.9
1615.7
0. CO 3491
462532.6
T7 26. 5
0. C02004
0.426
1.406
0.0255
0.807
0.0 237
3.743
10
501S62. 6
1753 .1
0.003525
501664.0
8731.6
0.001926
0.454
1-443
0. 0255
0.780
0.0234
3.721
11
541 117.2
1891 .0
0. C03521
540795.3
9722.4
0. 001848
0.475
1.463
0.0256
0.76B
0.0233
3.704
12
580271.9
2027 .5
0.CQ3450
579926.7
10702.8
0.001759
0.490
1.454
0. 0255
0.741
0.0231
3.673
13
61QC29.4
2125.9
0. C03056
609666.6
11656.7
0.001634
0.465
1.301
0.695
14
63019A. 1
2186 .8
0.002978
629819.3
11689. 3
0.001605
0*461
1.276
0.688
15
650358.7
2 245.7
0.C02E«2
649971.9
11721.1
C. 001543
0*461
1.234
0.665
16
67062 1.0
2302 .3
0.002788
670222.1
11751.9
C.00151C
0.458
1.2 09
0.655
17
69D883. 6
2358.5
0.002735
690472.7
11781.9
0.001466
0*463
1.193
0.640
la
711048. 3
2A13 .3
0.C0269O
710625.3
11811.1
C. 001420
0*472
1. 181
0.623
19
731212. 9
2467.2
). 002652
730777-9
11639.1
0.0)1356
).489
1.170
0.598
20
751377.5
2519.6
C. C02538
750930.6
11066.2
0.001332
0.475
1.126
0.591
21
771542.4
2570.9
0.C02543
771083.5
11692.3
0.001257
0,5)6
1.135
0.561
22
7917C7.0
2621.5
0. C02471
791236.1
11917.8
0,001268
0.487
1.108
0.568
23
811 871.6
2670.9
0.002421
811388.6
11942. E
0. 001216
0.493
1.091
0. 548
24
832133.9
2719.5
0.002397
831639.0
11967. C
0.001181
0*507
1.085
0.535
25
£52396.6
2767 .4
0.002346
851889.5
11990.2
0. 001133
0*517
1.068
0.516
26
872561. 1
2814.5
0. CC2320
872042.2
12013.5
0.0)1162
0 .499
1.061
0.531
27
892725. 8
2861. 6
0.C02346
892194.8
12035. 8
C. 001 052
0.552
1.078
0.4S3
28
91289C.4
2908.4
0. 002287
912347.4
12057.4
0.0)1085
0.526
1.055
0.501
29
933055.3
2954.5
0. 002282
932500.3
12079.4
0.001095
0.520
1.057
0.507
20
953219. 9
3C0J.3
0. C02224
952652.9
12101 .4
0.001083
0*513
1.035
0.504
21
973384.6
3044. 7
O.C02202
972805.6
12122. 8
0. 001043
0.527
1.029
0.487
22
993646. 9
3038.6
0.002147
993055.8
12143.9
0.001053
0*510
1.008
0.494
33
1013909.0
3 1 31 . 8
0. CC2133
1013306.0
12165. C
C. 001033
0*516
1.005
0.486
34
1C34074. 0
3174.8
0.002127
1053459.0
12185.6
0.001011
0.525
1.006
0.478
25
1054238.0
3217.0
0. 002054
1053611.0
12206.0
0.001011
0*508
0.975
0.480
36
1074403.0
3258.0
0.CO2008
1073764.0
12226.1
0.000987
0.509
0.957
0.47 0
STANTCN NUMBER RATIO BASFC a^ ST PT*0 .4=0 ,029 5*R EX** (- .2 >
STANTCN NUMBER RATIO FOR TH=1 IS CCNVERTED TO COMP/RAELE TRANSPIRATION VALUE
USING ALOGd + R)/B EXPReSSICM IN THE BLOWN SECTICN
173
RUN 120274 VELOCITY AND TEMPERATURE PROFILES
PEX =
0-14592E 06
REH
X
501.
REH
S
430.
XVO =
109.04 CM
. DEL2
s
0.064
CM. DEH2
3
0.055 CM.
UTNF =
11.62 M/S 0EL99=
0.468
CM. DELT99 =
0.479 CM.
Vise =
0.14911E-04 M2/S DELI
=
0.137
CM. UINF
=
11.
62 M/S
PORT =
19
H
=
2.130
Vise
= 0.
14931E-
04 M2/S
XLOC =
127.76 CM
. CF/2
* 0.15863E-02
TINF
3
17.
06 DEG C
TPLATE =
34.
06 DEG C
Y( CM. )
Y/OEL
U(M/S)
U/UINF
V +
U +
Y(CM.I T(DEG C)
TBAR
TBaft .
0.025
0.054
3,21
0.276
7.9
6.93
0.0165
31.77
0, 141
0.859
0.028
0.060
3.30
0.284
8.7
7.14
0.0191
30.65
0.211
0.709
0.030
0.065
3.36
C.289
9.5
7.27
0.0216
30.12
0.244
0.756
0.033
0.071
3.45
C.297
10. 2
7.47
0.0241
29.81
0.263
0.737
0.038
0.081
3-59
0.309
11.8
7. 76
0.0292
29.22
0.299
0.701
0.043
0.09 2
3.88
C.334
13.4
8.39
0.0343
28.65
0.335
0,665
0.051
0.100
4.19
0.361
15.8
9.05
0.0419
28.12
0.368
0.632
0.061
0. 130
4.48
C.3B6
18.9
9.68
0.0495
27.55
0.403
0.597
0.074
0.157
4.83
0,415
22.9
10.43
0.0597
26.99
0.438
0.562
0.089
0. 190
5.33
0.459
27.6
11.52
0.0724
26.42
0.473
0.527
0. 107
0,228
5.6 9
C.490
33.1
12.29
0.0851
25.80
0.512
0.486
0. 127
0.271
6.36
C.547
39.4
13.74
0. 1003
25.21
0.548
0.452
0. 150
0.320
7.02
0.604
46.5
15.17
0.1156
24.66
0.582
0.418
0. 175
0. 374
7,86
0.676
54.4
io.98
0.1334
23.87
0. 631
0.369
0.201
0.428
8.53
0.734
62.3
18.43
0.1537
23.07
0.681
0.319
0.226
0.483
9.13
0.786
70.2
19.73
0.1791
22.17
0.737
0.263
0.251
0.537
9.61
C.827
78.0
20.76
0.2045
21.39
0,784
0.216
0.277
0.591
9,98
C.859
85.9
21.56
0.2299
20.72
0.826
0.174
0.302
0.645
10,41
C.896
93.8
22.50
0.2553
20.10
0.864
0.L36
0.328
0.700
10.76
0,926
iOl.7
23.24
0.2807
19,56
0.896
0.102
0.353
0,754
10.90
C-938
109.6
23.56
0.3061
19.23
0.919
0.081
0.378
0.808
11. IC
0.955
117.5
23.99
0.3315
18.89
0.940
0.060
0,404
0.862
11.25
C.968
125.3
24.31
0.3569
16.61
0.957
0.043
0.429
0.917
U.3 5
C.977
133.2
24,52
0.3823
18.42
0.969
0.031
0.455
0.971
11.47
0.987
141.1
24.78
0.4077
18.30
0.976
0.024
0.480
1.025
11.51
C.990
149.0
24.87
0.4331
18.17
0.984
0.016
0.505
1.079
11.55
C.994
156.9
24.9/
0.4585
18.12
0.987
0.013
0.531
1.134
11.62
l.OOO
164.8
25. U
0.4839
16.05
0.992
0.008
0.509
18.00
0,995
0.00 5
0.535
17.98
0.995
0.004
0.560
17.95
0.998
0.002
0.585
17.92
1.000
0.000
RUN 120274 *♦* DISCRETE HCLE RI6 **♦ NAS-3-14336
STANTON NUHB6R DATA
TADB=
17.70
DEG C
U INFr
12.55 M/S
TINF* 17.64
DEG C
RHO =
1.202
KG/M3
Vise
= 0.14911E-04 M2/S
XVO» 109.1
CM
CP =
1012.
J/KGK
PR=
Oi7l7
***
520HSLFP P/0=10
PLATE
X
REX
TO
•REE NTH
STANTON NO
DST
DREEN
STCTHEO)
RATIO
1
127.8
Q.14482E
06
33.63
01428B4E
03
0.24237E-02
0.692E-04
39.
0.31299E-02
0.774
2
132.8
0.18417E
06
33. 62
C453195E
03
0.281 76 E-02
0.726E-04 ^
39.
0.29831E-02
0.945
3
137.9
0.22351E
06
'23. 65
0464285E
03
0.26203E-02
0.725E-04
39.
0.28698E-02
0.983
4
143.0
0.26 26 5E
06
33.65
C175171E
03
0.27133E-02
0.715E-04
40.
0.27782E-02
0.977
K
148,1
0.30220E
06
.33.63
0185625E
03
0.27025E-02
0.715E-04
40.
0.27018E-02
1.000
6
153.2
Q.34154E
06
33.65
Qi96241E
03
0.25923E-02
0.705E-04
40.
0.26364E-02
0.983
7
158.2
0.38088E
06
33.69
0110630E
04
0.25213E-02
0.698E-04
40.
0.25796E-02
0.977
8
163.3
0.42 02 3E
06
23.69
OU1602E
04
0.24206E-02
0.690E-04
40.
0.25293E-02
0. 957
g
168.4
0.45957E
06
;3. 65
0112550E
04
0.23988E-02
0.689E-04
40.
0.248456-02
0.965
10
173.5
0.49e91E
06
33.63
0*13489E
04
0.23739E-02
0.688E-04
40.
0.24440E-02
0.9 71
IL
178.6
0. 53 826E
06
33.65
C*14409E
04
0.23021E-C2
0.682E-04
40.
0. 240 7 2 E- 02
0.956
12
183.6
0.57760E
06
33 .*7
0;i5312E
04
O.Z2901E-02
0.6B0E-04
40.
0.23734E-02
0.965
12
187.5
Q.607S0E
06
32. 24
Oil5967E
04
0.201 78E-02
0.712E-04
40.
0.234966-02
0. 8 59
14
190.1
0.62776E
06
31.66
0a6390E
04
0.21461E-02
0.805E-04
40.
0. 233 42 E- 02
0.919
15
192.7
0.64802E
06
32.09
0il6822E
04
0.21198E-02
0.813E-04
40.
0.23195E-02
0.914
16
195.4
0.66838E
06
32. C9
0117251E
04
0.21015E-C2
C.799E-04
40.
0.23051E-02
0.912
17
198.0
0.68874E
06
32.07
0.17678E
04
0.21148E-02
0.805E-04
40.
0.22914E-02
0.923
IB
200.6
0.70901E
06
31.99
0a8107E
04
0.21121E-02
0.804E-04
40.
0.22781E-02
0.927
19
203.2
0.72927E
06
31.93
0il8532E
04
0.20924E-02
0.785E-04
40.
0.22653E-02
0.9 24
20
205.8
0.74952E
06
32.05
C.18957E
04
0.20866E- 02
0.799 E-04
40.
0.22529E-02
0.926
21
206.5
0.76979E
06
U.82
0a9380E
04
0. 20791E-02
0.763E-04
40.
0.22409E-02
0.928
22
211.1
C.79005E
06
31.82
0il96C8E
04
0.21458E-02
0.8 13 E-04
40.
0.22293E-02
0.963
23
213.7
0.81032E
06
31.97
0i2O229E
04
0.19965E-02
0.772E-04
40.
0.22181E-02
0.900
24
216.3
0 . 83 06 8E
06
;2.Q7
Oi20640E
04
0.20617E-02
0.802 E-04
40.
0.22071E-02
0.934
25
218.9
0.85104E
06
31.93
0121055E
04
0.20266E-02
0.779 E-04
40.
0.21964E-02
0.923
26
221.6
0.87130E
06
31.84
Oi21466E
04
0.204 80E-02
0.827E-04
40.
0.21861E-02
0.937
27
224.2
0.89156E
06
30.80
0i21886E
04
0.207416-02
0.743B-04
40.
0.21761E-02
0.9 53
28
226.8
0.91182E
06
31.68
0*22303E
04
0.20389E-02
0.831E-04
40.
0.216636-02
0.941
29
229.4
0.93208E
06
31. 82
Ci22722E
04
0.2C866E-02
0.781E-04
40.
0.21568E-02
0.967
30
232.0
0.95234E
06
32.^0
Oi23142E
04
0.20533E-02
0.804 E-04
40.
0.21476E-02
0.9 56
31
234.6
0.97261E
06
3 2. 20
0123554E
04
Q.2C084E-02
0.778E-04
40.
0.21385E-02
0.939
32
237.3
0.99297E
06
32. C5
0123960E
04
0.19943E-02
0.769E-04
40.
0.21297E-02
0.936
32
239.9
0. L0133E
07
32.03
0124363E
04
0.19780E-02
0.7 70 E-04
40.
0.21211E-02
0.933
34
242.5
0.10336E
07
31.78
0i24764E
04
O.19810E-O2
0.747E-04
40.
0.21127E-02
0.938
35
245. 1
0. 10539E
07
31.95
0125163E
04
0.19455E-02
0.783 E-04
40.
0.21 0456-02
0.9 24
36
247.8
0. 1074 IE
07
•21.65
012 554 8E
04
0. 18581E-02
0.82 9 E-04
40.
0.20965E-02
0.886
175
PUN
121074-1 CISCRETE HCLE
RIS *** NAS-3-
14336
STANTON NUMBER DATA
TADfl*
18.88
DEG C
U INF
IS
11.49 M/S
T INF* 18.82
DEG C
KHC*
1.202
KG/M3
Vise
* 0.14960E-04 M2/S
XVO* 109.1
CM
CPs
1011.
J/KGK
PR*
Oi716
***
520HSL40 M*0.4 TH
= 0 P/D
»1€ ***
PLATE
X
REX
TO
REE NTH
STANTON NO
DST
DR6EN
M
F
Ti'
THETA
1
127.8
0.143646
06
21.95
0*52290E
03
0.259C6E-02
0.8356-04
39.
2
132.8
0.18266E
06
21. 95
C463028E
03
T. 291266-02
0. 8636-04
39^
0.42
0.0034
20i76
0.147
3
137.9
0.22169E
06
31.95
0.76327E
03
0.291 C8E-02
0.8636-04
39.
0.00
0.0034
31i95
0.147
4
143.0
0.26071E
06
21. 95
0189115E
03
0.26511E-02
0.8406-04
39.
0.42
0.0054
2li09
0.173
5
148.1
0.29973E
06
31.95
0.10194E
04
0.27423E-02
O.848E-04
40.
0.00
0.0034
3U95
0.173
6
153.2
0. 23 07 5E
06
21.97
CU1442C
04
0.24729E-02
0.824E-04
40.
0.42
0.0034
2 iao
0.173
7
15 B. 2
0.37778E
06
31.95
0il2666E
04
0.263C56-02
0.8 38E-04
40.
0.00
0.0034
31i95
0.173
8
163.3
0.41680E
06
31.97
Q-13891E
04
0.2480 7E-02
0.825E-04
40.
0.42
0.0034
21^19
O.IBO
9
168.4
0.45582E
06
21.99
CU5C99E
04
0.24966E-02
0.825E-04
40.
0.00
0.0034
31i99
0.160
10
17 3,5
0.49484E
06
21.97
0U6286F
04
0.22724E-02
0. 816E-04
40.
0.42
0.0034
2U23
0.183
11
178.6
0.53387E
0 6
21.95
C.17457E
04
0.24021E-02
0.819E-04
40.
0.00
0.0034
31.95
0.183
12
183.6
0.572B9E
06
21.97
0.18613E
04
0.229 31E-02
0.8106-04
40.
0.42
0.0034
21.27
0.186
13
187.5
0-6025 5E
06
20.59
0il9523E
04
0.21369E-02
0,7776-04
41 .
14
190,1
0.62264E
06
i0,2i
0;20206E
04
0.21949E-02
0. 6736-04
41.
15
192.7
0.64 27 4E
06
20. 50
C4206446
04
0.21670E-02
0.8716-04
41 .
16
195.4
0. 662936
06
30. 5C
0i2lO80E
04
0.216186-02
0.860E-04
41.
17
198.0
0.68313E
06
20. 50
C*21516E
04
0.2170 7E-02
0.8666-04
41.
18
200.6
0.70322E
06
30.44
0*21954C
04
0.21862E-02
0.872E-04
41.
19
203.2
0.72332E
06
20.38
3i22390E
04
0.2145CE-C2
0.8446-04
41.
20
205.8
0.74342E
06
30.46
Oi22825E
04
0.21768E-02
0.8616-04
41.
21
208.5
Q.76351E
06
20.42
0i23253E
04
0.20816E-02
0.827E-O4
41 .
22
211.1
0.7336 IE
06
30.48
0423676E
04
0.21244E-02
0.8586-04
41.
22
213-7
0. eC37lE
06
30.44
0 12409 7E
04
0. 206236-02
0.832E-04
41,
24
216.3
0.82390E
06
20.48
C-24520E
04
0.214I6E-02
0.869E-O4
41.
25
213.9
0. 84410E
06
20.42
C124945E
04
0.20792E-02
0.8456-04
41.
26
221.6
0.86419E
06
20, 21
Ci2536“iE
04
O,21110E-O2
0.889E-04
41.
27
224.2
0.88429E
06
29.50
0.25791E
04
0.21105E-02
0.8156-04
41.
26
226.8
0.90439E
06
20.25
C126215E
04
0.20973E-C2
0.890E-04
41.
29
229.4
0.92448E
06
30. 33
0*26642E
04
0.2 15 COE- 02
0.846E-04
41.
30
232.0
0. 9445 8E
06
20.65
0i27C70t
04
0.21022E-02
'J.865E-04
41.
31
234.6
0-96468E
06
30,65
0J27487E
04
0.204656-02
0.833E-04
41.
32
237.3
C.98487E
06
30.56
0i27897E
04
0.20273E-02
0. 8286-04
41 .
33
239,9
0.1005LE
07
30,50
Cl28305E
04
0.2C261E-02
0.826E-04
41.
34
242.5
0.10252E
07
20.33
Ci28710E
04
0.20017E-02
0.7996-04
41.
35
245.1
0.104536
07
20.46
Qi29110E
04
0.19746E-02
0.8426-04
41 .
36
247.8
0.1065 4E
07
20.17
0129500E
04
0.1E951E-02
0.8086-04
41.
UNCERTAINTY IM REX=195LI, UNCERTAINTY IN F = 0, 05155 IN RATIO
DT^
0.023
0.024
0.025
0.024
0.023
0.024
0.023
0.024
0.023
0.024
0.023
RUN 121074-2 DISCRETE HCLE RIG NAS-3-14336
STANTCN NLWBER DATA
TADB=
18.94
DEG C
U INF
11.49 M/S
TINF= 18.88
DEG C
RhO=
1.202
KG/M3
Vise
= 0.14965E-04 M2/S
XVQs 109.1
CM
CP =
1011 .
J/KGK
PR =
01716
***
520HSL40 M-0.4
► TH
= l P/C
= 10 ***
PLATE
X
REX
TO
REE NTH
STANTON NO
DST
DREEN
M
F
T2
THETA
DTH
1
127.8
0.14361E
06
32.57
Ci52278E
03
0. 248726-02
0.7986-04
39.
2
132.8
0.18262C
06
22.58
Ci62237E
03
0.261 85E-02
0.8076-04
39.
0.42
0.0034
32i27
0.977
0.023
3
137-9
0,22 163E
06
32..60
0.85152E
03
0.25181E-02
0. 7986-04
40.
0.00
0.0034
32160
0.977
0.023
A
143-0
0. 2606 5E
06
22.60
0il0750E
04
0.23261E-02
0.783 E-04
40.
0.37
0.0030
31134
0.908
0.022
5
148.1
0.29966E
06
22.58
0.12698E
04
0. 2260 ie-02
0.779E-04
40.
0,00
0.0030
32158
0.908
0.023
6
153.2
0. 33 86 76
06
22. 60
0-14607E
04
0 .21201E-02
0.768E-04
41.
0.39
0.0032
31126
0.902
0.022
7
158.2
0.37769E
06
22.60
0416558E
04
0.2156.1E-02
0.770E-04
41.
0.00
0.0032
32160
0.902
0.023
8
163.3
0.41670E
06
32.60
0*18504E
04
0.209696-02
0-766 E-04
41.
0. 32
0.0026
31161
0.928
0.022
9
163.4
0.455J1E
06
22. 58
Ci20236£
04
0.2C237E-02
0.762E-04
41.
0.00
0.0026
32158
0.92 8
0.023
10
173.5
0.49473E
06
22.58
0i21945E
04
0.196126-02
0.7576-04
42.
0.39
0.0031
31103
0.887
0.022
11
178.6
0.533746
06
22. 62
0*23 78 IE
04
0.19052E-02
0.752E-04
42.
0,00
0.0031
32 4 62
0.B67
0.023
12
183.6
0.572.75E
06
32.58
0i25597E
04
0.166476-02
0.7516-04
42.
0.34
0.0027
30188
0.875
0.022
13
187-5
0.60240E
06
21.46
0J.27116E
04
0.21799E-02
0.725 E-04
42.
14
190.1
0.62250E
06
32.97
0i2 8416E
04
0. 143566-02
0.6896-04
42.
15
192.7
Q.64259E
06
23. 21
0i28735E
04
0. 174056-02
0.699 E-04
42.
16
195.4
0.66278B
06
23.21
Ci29C86E
04
0.175206-02
0.694E-0V
42-
17
198.0
0.682fl7E
06
23.20
Ci29442E
04
0. 178276-02
0.7056-04
42.
16
200-6
0.703066
06
23. 14
0.29801E
04
0.178736-02
0.707E-04
42 .
19
203.2
0-72315E
06
23. 10
0.30159E
04
0 .177225-02
0.691E-04
42.
2C
205.8
0.74324E
0 6
23.18
C.30520E
04
0. 1E16OE-02
0.7096-04
42.
21
208.5
0.763336
06
33. 16
0i3O875E
04
0.172006-02
0.6816-04
42.
22
211.1
0.78342E
06
23. 12
0*312296
04
0 .179646-02
0.714E-04
42.
23
213.7
0-80352E
06
23. C4
0*3158PE
04
0. 177556-02
0.6976-04
42.
24
216.3
C.82371E
06
33. 23
0.31944E
04
0.176296-02
0.717E-04
42.
25
218.9
0,84390E
.06
23. 12
C-323C0E
04
0. 177376-02
0.708E-04
42 .
26
221.6
0. E6399E
06
22.95
C*32661L
04
0.18175E-02
0.744E- 04
42.
27
224-2
0.88408E
06
22. 24
C.33019E
04
0.17406E-02
0.661E-04
42.
2d
226.8
0.90417E
06
33.08
0*33371E
04
0.17576E-C2
0.7376-04
42.
29
229.4
0.92426E
06
23. CO
0*33729E
04
0.1E053E-02
0. 7006-04
42.
30
232.0
0.944356
06
33. 27
0.34093E
04
0.181C8E-02
0. 7296-04
43.
31
234.6
0. 96445E
06
23. 29
Oi34451E
04
0.17505E-02
0.706 6-04
43.
32
237.3
0.98464E
06
23.08
0i34806E
04
0. 17774E-02
0.704E-04
43 .
33
239.9
C. 1004 86
07
23.10
0*35159E
04
0.17362E-02
0.701 E-04
43 .
34
242.5
0.10249E
07
22.67
C*35509E
04
0.173 7.7E-02
0.678E-04
43.
3 5
245.1
0-10450E
07
33,02
C*35855E
04
0.170406-02
0.717E-04
43.
36
247-8
0.1065 IE
07
22.66
0*36196E
04
0.168706-02
0.758 E-04
43 .
UNCERTAINTY IN R,ex = 19507.
UNCERTAINTY IN F=0,05155 IN RATIO
177
RUN 12107A-1 ♦♦♦ DISCRETE HCLE RI€ *♦* NAS-3-14336
520HSL40 M=0-4
RUN 121074-2 DISCRETE HCLE Rl€ ♦** NAS-3-14336
STANTCN NU^IBER DATA
Th=0 P/D=10 *t*
STANTCN NUMBER DATA
*** 520HSL4C M=0-4 TH=1 P/0=10 ***
LINEAR SUPERPOSITION IS APPLIED TO STANTON NUMBER DATA FRCI“
RUN
NUMBERS 121074-1 AND
121074-2 TO
1 OBTAIN STANTON NUMBER DATA AT
TH*0 AND TH=1
PLATE
FEXCOL RE
CEL2
ST(TH=0)
REXHOT
RE DEL2
ST(TH=1)
ETA
STCO
F-COL
STHR
=-Hor
LOGS
1
143641.8
522.9
0.002591
142607.7
522.8
0. 00248 7
UUUUJ
1.069
0.0000
1.026
0,3000
1.026
2
182664.3
631.3
0.002965
182620.9
622.2
0.002610
0*120
0.992
0.0034
0. 873
0.0034
1.361
3
221686.8
747,3
0. 002980
221634.1
854. C
0.002507
0.159
1.036
0.0034
0.872
0.0034
1,377
4
260709.3
858.5
0.002718
260647.4
1079.6
0.002302
0.153
0.976
0,0034
0.827
0.3030
1.288
5
299731. 8
967.2
0.C02856
299660.6
1283.7
0.002200
0.230
1.055
0.0034
0.812
0.0030
1.284
6
333754.4
1072.8
0.002556
336673.9
1463.2
0.002074
0.189
0.967
0.0034
0.785
0,0032
1.294
7
377776. 9
1176.2
0.002743
377687.1
1668.2
0.002093
0*237
1.061
0.0034
0.809
0.0032
1.330
8
416799.4
1279 .9
0.002572
416700.3
1892.9
0.002053
0*202
1.015
q , 0034
O.BIO
0.0026
1.249
9
455821.9
1381.0
0.002610
455713.6
2071.7
0.001978
01242
1.048
0. 0034
0. 794
0.0026
1.243
10
494844.4
1480.3
0.C02475
494726.8
2247.6
0.001909
0.229
1.011
0.0034
0.779
0.3031
1.316
11
533866. 9
1577.9
0.002531
533740,0
2442.6
0.001825
0*279
1,049
0.0034
0.757
0.0031
1.298
12
572889.4
1674.3
0. C024C7
572753.3
2635.0
0.001792
0.256
1.012
0.0034
0.753
0.0027
1.241
13
602546.6
1742.6
0.002125
602403.4
2798,9
0.002187
•♦***
0.903
0.929
14
622643. 1
1788.1
0.002396
A22495.2
2940,9
0,001306
0.455
1.024
0.558
15
642739.8
1835.2
0.002260
6^2587.0
2970.8
0.001668
0*269
0.981
0.717
16
66 2933.6
1880.9
0.002270
662776.1
3004.5
0.001682
0.259
0.983
G.728
17
683127.9
1926.6
0.C02273
682965.5
3038.7
0.001717
0.245
0.990
8.747
18
70322A.4
1972.6
0.002292
703057.3
3073.2
0.001719
0*250
1.004
0.753
19
723321.0
2018.2
0.002244
723149,1
31 07.7
0.001709
0.238
0.988
0.753
20
743417.6
2063.6
0.002272
743240.9
3142.6
0.001755
0*228
1.006
0.777
21
76351A.4
2108.4
0.002177
763333.0
3176.9
0.001658
0*238
0,970
0.738
22
783611.0
2152.6
0.002211
783424.8
3211.1
G. 001740
01 213
0.990
8.779
23
803707.6
2196.3
0.002138
803516.6
3245.9
0.001727
0*193
0.962
8.777
24
823901.5
2240 .4
0.002242
823705.7
32 80.4
0.001698
01242
1.014
8.768
25
844095.7
2284.7
0.002160
843895.1
3314.8
0.001722
0*203
0.981
0.782
26
864192.3
2323.4
0.002189
863986.9
3349.9
0,001767
0*192
0.999
0.807
27
E8A288.8
2372.7
0.002208
884076.7
3384.5
0.001678
01240
1.013
0.769
28
904385.4
2416.9
0.C02187
904170.5
3416.5
0.001700
01223
1.008
0.783
29
924482.3
2461.4
0.002241
924262.6
3453.1
0.001747
01221
1.037
8.808
39
944578.8
2505.9
0.002179
944354.4
3486.4
0.001761
01192
1.013
8.8IB
31
964675.4
2549.2
0.002127
964446.2
3523.2
0.001700
0*201
0.993
0.793
32
984669.3
2591.7
0.002094
984635.3
3557.8
0.001735
01171
0.981
0.813
33
1005063.0
2633.9
0.002103
1004824.0
3592,2
0.001687
01198
0.989
8.794
34
1025160.0
2675.9
0.002072
1024916.0
3626.2
0.001693
01183
0.978
0.799
35
1045256.0
2717.3
0.002046
1045008.0
3659.9
0.001658
01189
0.970
0.786
36
1065353.0
2757.5
0.001950
1065100.0
3693.2
0.001651
01153
0.928
0. 786
STANTON NUMBER RATIO BASEC ON ST*PR4*0.4«0.029S*REX4*(-.2)
STANTON NUMBER RATIO FOR 1H«1 IS CONVERTED TO COMPARABLE TRANSPIRATION VAUE
USING AlOGIl * BI/8 EMPRESS ION IN THE BLONN SECTION
RUN 120574-1 *** DISCRETE HOLE RI6 *** NAS-3-14336
STANTGN NUMBER DATA
H
CO
TAC8*
19.95
DEG C
UINF
=
1J.52 M/S
TINF= 19.89
DEG C
RHO*
1.201
KG/ M3
V ISC
* 0.15027 F-04 M2/S
XVC= 109.1
CM
CP»
1010.
J/KGK
PR =
0*715
520HSL80 M*0.8 TH
-0 F/C
=10
PLATE
X
REX
TO
REENTh
STANTCN NO
OST
DRE6N
M
F
T2
THETA
or^
1
127.8
0.1433 IE
06
22. 55
0152170E
03
0.2E012E-02
0.879E-04
39.
2
132.8
0.18225E
06
32.55
0163470E
03
0.3C034E-02
0.897E-04
39.
0. 81
0.0065
21*82
0.153
0.024
3
137.9
0.22 11 8E
06
22. 57
Ci79l63E
03
0.30626E-02
0.901 E-04
39.
0.00
0.0065
32157
0.153
0.024
4
143.0
0.26011E
06
32-53
0194 5 83E
03
0.28626E-02
0.B85E-04
40.
0.82
0.0066
22109
0.174
0.024
5
148.1
0.29904E
06
32.55
0m030E
04
0.29117E-02
O.089E-O4
40.
0,00
0.0066
32155
0.174
0.025
6
153.2
0.33798E
06
22. 55
Cil2572E
04
0.27089E-02
0.871E-04
41.
0.81
0.0066
22104
0.170
0.024
7
158.2
0.37691E
06
32.57
Cil4074E
04
0.27737E-02
0.8756-04
41.
0. 00
0.0066
32157
0.170
0.024
6
163.3
0.415B4E
06
22.53
0415566E
04
0.26571E-02
0.867E-04
41.
0. 81
0.0066
22110
0.175
0.024
9
168.4
0.45478E
06
32.53
0117 044E
04
0.26383E-02
0.866 6-04
42-
0.00
0.0066
32i53
0.175
0.025
10
173.5
0.49371E
06
22. 51
0U8516E
04
0.26265E-02
0.8666-04
42.
0.81
0.0066
22110
0.175
0.024
11
178.6
0.53264E
06
32.55
0il9992E
04
0.26551E-02
0.866E-04
42.
0.00
0.0066
32*55
0.175
0.025
12
183.6
0.S7158E
06
32.55
Ci2I454E
04
0.25573E-02
0.858E-04
43.
0.82
0.0066
22112
0.176
0.024
13
187.5
0.60117E
06
31.13
0422636E
04
0.23024E-02
0.837E-04
43.
14
190.1
0-62122E
06
30. 82
Q123560E
04
0.23921E-02
0.947E-04
43.
15
192.7
0.6412 7E
05
31. GC
0124036E
04
0.237246-02
0.9486-04
43,
16
195.4
0.66 14 IE
06
21-00
0124514E
04
0.2367.7E-02
0.938 E-04
43.
17
198.0
0.68156E
06
21.00
C124990E
04
0.23727E- C2
0.942E-04
43.
18
200.6
0.70161E
06
30.96
Oi25465E
04
0.2365 7E-02
0.941E-04
43.
IS
203.2
0.72 166E
06
20.92
0425937E
04
0.23370E-02
0.919E-04
43.
20
205.8
0.74171E
06
30. 96
0126412E
04
0.2394 8H-02
0.942E-04
43.
21
206.5
C.76176E
06
30. 90
0126884E
04
0.23003F-02
0.908 E-04
43.
22
211.1
O.TSiaiE
06
30-98
012734 7E
04
0.23209E-02
0.935E-04
43.
23
213.7
0.E0186E
06
20.92
0127810E
04
0.22854E-02
0.913E-04
43.
24
216.3
0.82201E
06
21. CO
0*28272E
04
0.23276E-02
0.944E-04
43.
25
218.9
0.84216E
06
30.90
0128739E
04
0.23221E-02
0.9316-04
43.
26
221.6
0.86221E
06
20. 62
C129204E
04
0.231 04E-02
0.969 E-04
43.
27
224.2
0.88226E
06
30.00
0129667E
04
0.23006E-02
0.686E-04
43.
28
226.8
0.9023 IE
0 6
20.86
0430129E
04
0.22979E-02
0.971E-04
43.
29
229.4
0-92236E
06
30. 80
0130596E
04
0.23571E-02
0.922E-04
43.
30
232.0
0.9424 IE
06
21. 15
0131063E
04
0.22998E-02
0.942 E-04
43.
31
234.6
0.96 246E
06
21.13
0131520E
04
0.22515E-02
0.909E-04
43.
32
237.3
0.98261E
06
31.02
0i3l97lE
04
0.2239BE-02
0.905E-04
43.
33
239.9
0.10028E
07
21. 02
C132418E
04
0.22125E-02
0.902E-04
43.
34
242.5
0.10228C
07
30.80
C432861E
04
0.22035E-02
0.8 74E-04
43.
35
245.1
0.10429E
07
20, 94
C.33302E
04
O-21820E-O2
0.920 E-04
43.
36
247.8
0.10629E
07
30.69
0l33728E
04
0. 206816-02
0.9586-04
43.
UNCERTAINTY IN ftEX=L9467. UNCERTAINTY IN F=0-05154 IN RATIO
179
RUN 120574-2 *** DISCRETE HCLE RIG NAS-3-14336
STANTCN NUMBER CAT A
TADB=
19.71
CEG C
U INF
X
11.57 M/S
TINF= 19.65
DEG C
RHO*
1.202
KG/M3
Vise
= 0.150C6E-04 M2/S
XVC» 109.1
CM
CP»
1010.
J/KGK
PR=
0.715
520HSL80 M=0,8 TH
= 1 P/C
= 10 Hi**
PLATE
X
REX
TO
PEENTF
STAMCN NC
CST
OREEN
M
F
T2
THETA
DTH
1
127.3
0. 144.1 2E
06
32.67
0.524656
03
0.26996'=-02
0.834E-C4
39.
2
132.8
0.18327E
06
32.67
C.63126E
03
0.27465E-02
0.8386-04
40.
0.76
0.0062
32128
0.955
0.023
3
137.9
0.22243E
06
22.87
0fc97i05E
03
0.2786SG-02
0.8426-04
41.
0.00
0.0062
32.87
0.955
0.023
4
143.0
0. 26 1 5 8E
0 6
32. 85
0.13074E
04
0.25702E-02
0.825E-04
42.
0.80
0.0065
3U88
0.927
0.023
5
143.1
0.30073E
06
32.83
0»16429E
04
0. 253C4E-0Z
0.822E-C4
43 .
0.00
0.0065
32.83
0.9 27
0.024
6
153.2
0. 23988E
06
32. 87
a*19733f
04
0.22100E-02
0.803E-04
44.
0.81
0.0066
31^92
0.92 8
0.023
7
158.2
0.279Q4E
06
32. 63
0.23046E
04
0.240346-02
0.812E-04
45 •
0,00
0.0066
32*83
0.928
0.024
e
163.3
0.41619E
06
32.65
Ci26353E
04
0.22795E-02
0.802E-04
46 •
0.76
0.0061
31i85
0.924
0.023
9
168.4
0.45734E
06
32. 87
C*29461t
04
0.22885E-02
0,801E-04
47.
0.00
0.0061
32187
0.924
0.023
10
17 3.5
0.4965QE
06
3 2.89
0.32554E
04
0.220096-02
0.794E-04
48.
0. 82
0.0067
31l54
0.898
0.023
11
178.6
0.53565C
06
32.87
3i35771E
04
0.22627E-r2
0. 7996-04
49.
0,00
0.0067
32*87
0.898
0.023
12
183.6
0.57480E
06
32.87
0.389886
04
0.2199 8E-02
0.795E-04
50.
0.86
0.0069
31.42
0.891
0.023
12
13 7.5
0.60456E
06
31. 55
Ci42043E
04
0.2C756E-02
fJ.76lE-04
51-
14
190.1
0.62472E
06
31.23
0*44686E
04
0.21724F-02
C. 660E-04
51 .
15
192.7
0.d4468E
06
31. 44
0i45321E
04
0.213266-02
0.858E-Q4
51.
16
195.4
0.66515E
06
21.44
0:45753E
04
0.21500E-02
0. 853E-C4
51.
17
198.0
0.6854ie
06
31.44
0*46189E
04
O.21601E-O2
0.862E-04
51.
18
200.6
0.70557E
06
21.40
C.46627E
04
0.21691E-02
0.863E-04
51.
19
203.2
0.725736
06
31.36
0*47062E
04
0,21411E-C2
0.843E-04
51.
20
205.8
0.74590E
06
31.40
Oi47502E
04
0.22098E-02
0.867E-04
51.
21
208.5
C.76606E
06
21.26
0.47934E
04
0.2C719E-02
0.830E-04
51.
22
211.1
0. 78623E
06
31.23
0*48370E
04
0.22492E-U2
0. 8836-04
51.
23
213.7
0-80639E
0 6
31,34
0*48309E
04
0.2C950E-02
0.843E-04
51.
24
216.3
C.82665E
06
31.46
Qi49237E
04
0.214516-02
0.870E-04
51.
25
218.9
0.84691E
06
21.38
C.49670E
04
0.Z1461E-02
0. 8616-04
51.
26
221.6
C.86708E
06
31,26
0a5O1O56
04
0.21629E-02
0.899E-04
51.
27
224.2
0.68724E
■06
20. 50
Ci5Q536E
04
0.21083E-02
0.811E-04
51.
26
226.8
0.90740E
06
21.32
0i50963E
04
0. 212246-02
0.894F-04
51.
29
229.4
0.92757E
0 6
3 1 • '2 6
0.51396E
04
0.216886-02
0.849E-04
51.
30
232.0
0.S4773E
06
21.55
0*51833E
04
0.21602E-02
0.878E-04
51.
31
234.6
3.S6789E
06
31. 57
Oi52260E
04
0.2C685E-02
0.841 E-04
51 .
32
237.3
0.98816E
06
21.38
Oi5266CE
04
0.20894E-02
0.842E-04
51.
32
239.9
C.10084E
07
31. 22
0.53102E
04
0.20903E-02
0.843 E-04
51.
34
242.5
0.10286E
07
31.21
C*53517E
04
0.2C230E-02
0.807E-04
51.
35
245.1
0.1048 7 E
07
31.32
0153926E
04
0.202756-02
0.851E-04
51.
36
247.8
0.10689E
07
31. 11
Ci54325E
04
0.1S295E-02
0.887E-04
51.
UNCERTAINTY IN PSX=1957i. UNCERTAINTY IN F=0. 05151 IN RATIO
180
RUN
120574-1
OISCRETI
HOLE RIG
*** NAS-3-14336
STANTON NUMBER
DATA
S20HSLB0 M-0.8
TH«0
P/D«10
RUN
120574-2
*♦* DISCRETE
HCLE RIG
NAS-3- 14336
STANTCN HUMBER
DATA
***
520HSL80 M-O.e
TH«l
P/0*lO **♦
LINEAR SUPERPOSITION IS APPLIED 10 STANTON NUMBER CATA FRCM
RUN
NUMBERS 120574
-1 AND
120E74-2 TO
OBTAIN STANTON NUMBER DATA AT
TH-0 AND
TH = 1
PLATS
REXCOL RE
0EL2
STITH=OI
REXHOT
RE 0EL2
ST(TH*l)
ETA
STCR
F-COL
5THR
F-HOT .
LOGS
I
143312.5
52L.7
0. C02801
144121.1
524.6
0. 002700
UUUUU
1 .156
0.0000
1. 114
0.0000
1.114
2
182245.5
635.7
0.C03052
183273.8
631.0
0.002732
0.105
1.020
0.0065
Q.914
0. 0062
1.750
3
221178.6
755.7
0.003U5
222426.5
981.0
0.002771
0.110
1.082
0.0065
0.964
0.0062
1.834
4
260111. 6
873 .3
0.C02924
261579.3
1327.5
0.002548
0.129
1.049
0. 0066
0.915
0.0065
1.842
5
299344.5
988 .6
0.-003000
300731.9
1680.5
0.002493
0.169
1.107
0.0066
Q.921
0.0065
1.871
6
337577. 7
1101.5
0.002600
339884.6
2028.2
0.002272
01189
1.059
0. 0066
0.660
0.0066
1.831
7
376910. 7
1211.6
0. C02657
379037.4
2376.5
0.002366
0.171
1.104
0.0066
0.916
0.0066
1.915
6
415843. 6
1320.6
0.C02744
418190.1
2724.4
0.002242
01183
1.061
0.0066
8.835
0.0061
1.835
9
454776. B
1427.0
0.C02720
457342.8
3052.0
0.002253
0*172
1.091
0.0066
0.905
0,0061
1-873
10
493709.8
1533.0
0.002728
496495.5
3377.7
0.002149
0*212
1.113
0.0066
0.878
0.0067
1.929
IL
532642. 9
1639.7
0. C02750
535648.2
3724.0
0.002207
0.197
1. 139
0.0066
0.915
0. 0067
1.987
12
571575.9
1744.7
0.002645
574800.9
4070.3
0.002147
0.188
l.lll
0. 0066
0.903
0.0069
2.021
13
601165. 1
1819.8
0.C02358
604557.1
4404.1
0.002042
0.134
1.001
0.868
14
621215.6
1868.1
0, C02446
624720.7
4717.4
0.002140
01125
1.045
0.915
15
641266.1
1917.0
0.00 2431
644884.3
4760.2
0.002097
0.137
1.045
0.903
16
6£1«12. 7
1965.7
0.002421
665145.6
4802,7
0.002118
0.125
1.047
0.917
17
681561.6
2014,3
0.002423
685407.2
4845.7
0.002138
0. 118
1.054
0.931
18
701612. 1
2062.9
0. 002414
705570.8
4888.9
0.0)2140
0.113
1.056
0.938
19
721662.6
2111 .0
0.002383
725734.4
4931.9
0.002119
0.111
1.049
0.934
20
741713. 1
2159.4
0.CC2440
745898.1
4975.3
0,0)2183
01106
1.080
G, 967
21
761763.9
2207.6
0. C02256
766C62.0
5017.9
0.002038
Oil35
1.048
0.908
22
781814.4
2254.7
0.002338
786225.6
5061.1
0.002239
0*043
1.046
1.0)2
23
801864.9
2301 .6
0.C02332
EC6389.3
E1C4.5
0.002067
0.114
1.048
G.930
24
822012.5
234&.B
0.002372
626650.5
5146.6
0.00211 6
0.107
1.072
0,958
25
8^2160.4
2 396 .4
0.002365
846912.1
5189.6
0.002120
0*104
1.074
0.963
26
862210,9
2443 .6
0,002346
867075.8
5232.6
0.002 141
0.08 7
1.070
0.978
27
882261.4
2490.8
0. 002348
887239.4
5275.2
0.002080
0.114
1.076
0.954
28
902311.9
2537 .8
0. 002341
907403.0
531 7.3
0. 002097
0*104
1.077
0.966
29
922362.7
2585.4
0.C02403
927566.9
5360.1
0.0)2141
0.109
1.111
0.991
30
942413.2
2633.0
0. CO 2 3 34
947730.6
5403.3
0.002140
0.033
1.084
0.994
31
962462. 6
2679.5
0. 002296
967894.2
544 5.5
0.002042
O.lll
1.071
0.953
32
982611. 3
2725.4
0. C02277
9B8155.4
54E7.C
C. 002 06 7
0 1092
1.066
0.96 9
33
1002759. 0
2 770.7
0.002242
1008417.0
5528.8
0.002072
0.076
1.0 54
0.975
34
1022809.0
2815.8
J. 002248
1028580.0
5569.8
0.001996
0.U2
1.061
0.943
35
1042860.0
2860 .6
0.002221
1040744.0
5610.2
0.002005
0 . 09 7
1.052
0.951
36
1062910. 0
2904.0
7, C021C2
1068907.0
5649.7
0.001909
0.)92
l.JO)
0,909
STANTON NUMBER RATIO BASSE ON ST*PR**0 ,4=0 .029‘5 + REX-f * (- .2 )
STANTON NUMBER RATIO FOR TH = 1 IS CCNVERTEO TO COMPARABLE TRAN SP IR ATIDN \/ALJE
LSING ALCGd + BI/P EXPRESSICN IN THE Bl OWN SECTION
Appendix II
SPANWISE PROFILE DATA
Contained In this appendix Is a numerical tabulation of the Spanwlse
profiles that are discussed In Section 3.4, and plotted In Figures 3.23
and 3.24 for velocity, and Figures 3.27 through 3.30 for temperature.
Note that the same velocity profile points accompany the 0 ■* 1 and,
6 “ 0 temperature profiles. See Appendix I for the computer listing
nomenclature.
RUN 092974/100374
SPANWI S£ PROFILE
It
X
Ui
REX =
O.IOCOOE 01
REM =
6833.
REH
=
10259-
xvo =
0.00 CP
DEL2 =
0.626
CM DEH2
0.
934 CM
UINF =
16.71 H/S 0EL99=
3.629
CM 0ELT99 =
4.
066 CM
Vise ^
0.15323E-04 W2/S DELI =
1.048
CM UINF
=
16.
67 M/S
PORT
1
H
=
1.672
Vise
= 0.
15175E
-04 M2/S
XLOC =
1 76.40 CP
CF/2 = O.iOOOOE 01
TINF
=
21
.25 DEG <
TPLATE =
36
. 82 DEG 1
V(CM)
Y/DEL
U(M/S)
U/UINF
7*
U+
YlCMi T(DEG C)
TBAR
TBAR
0.025
0.007
4.86
0.291
277.0
0.29
0.0546
34.98
0. 118
0.882
0.028
0. 008
5.00
0.299
3 04. 7
0.30
0.0571
34.66
0. 139
0.86 1
0.030
0,006
5.22
0.312
332 .4
0.31
0.0597
34.54
0. 146
0,854
0.033
0.009
5.42
0.324
360.2
0.32
0. 0648
34.28
0. 163
0.83 7
0.038
0.010
5.73
0.343
415. 6
0.:>4
0.0724
34.06
0. 178
0.822
0.046
0.013
6.14
0.367
496.7
0.37
0.0825
33.76
0. 196
0,804
0.056
0.015
6.49
0.388
609.5
0.39
0.0952
33.49
0.214
0.786
0.069
0.019
6.80
0.407
/46 .0
0.41
O.i 105
33.26
0.228
0.772
0. 064
0.023
7.13
0-427
914.2
0.43
0. 1308
33 .02
0.244
0.756
0.IQ2
0.028
7.40
0.442
1108 .2
0.44
0.1562
32.80
0.258
C.742
0. 122
0.034
7.63
0.456
1329,8
0.46
0.166/
32.61
0.270
0.730
0. 147
0.041
7.86
0.47 0
Id Jo • 8
0.47
0.2222
32,46
0. 280
0.72 0
0. 178
0.049
8. 08
C.484
1939.3
0.48
0.2629
32,36
0.285
0.715
0.213
0.059
8.24
0.493
232 7.1
0.49
U.3U86
32.32
0, 289
0.71 1
0.254
0.070
8.37
0.501
27 70.4
0.50
0.3619
32.35
0.287
0.713
0.300
0.083
8.45
0.505
3269.1
0.51
0.4254
32.27
0,292
0.708
0.351
0.097
8.47
0.507
.3623 . 1
0.51
0.4889
32.30
0.290
0.710
0.406
0. 112
8.4 7
C.507
4432 .6
0.31
0.5524
32.28
0.291
0.709
0.467
0. 129
8.44
0.505
5097.5
0.51
0.6159
32.19
0. 298
0.702
0.538
0. 148
8.4 1
0. 503
5o73. 2
0.5O
0.6794
32.15
0.300
0,700
0.620
0.171
8.36
C. 500
o7 39 • 8
0.50
0.7429
31.96
0.312
0.688
0.696
0. 192
8.41
0.503
7590.9
0.50
0.8064
31 .91
0.315
0.685
0.772
0.213
8.46
0.508
6422 .0
0.51
0.8699
31.70
0. 329
0-671
0.848
0.234
8.68
0. 519
9253.1
0.52
0.9334
31.57
0.337
0.663
0.925
0.255
8.87
0.53110084.2
0.53
1.0604
31.47
0.344
0.656
1.026
0.283
9.26
0.55411192.4
0.55
1.1874
30.90
0.381
0.619
1.128
0.311
9.65
0.5781<t:300 ,5
0.58
1.3144
30,26
0,421
0.57 9
1.229
0.339
10. 08
0.60313406 . 7
0.60
1.4414
29.67
0.459
0.54 1
1.356
0.374
10.52
0.63014793.9
0.63
1.5684
28.89
0.510
0.490
1.483
0.409
10.92
0.65316179.1
0.65
1.8224
28.18
0.555
0.44 5
1.610
0.444
11.26
0.67417564.3
0.67
2.0764
26.99
0.632
0.368
1.737
0.479
11.65
0.69718949.5
0.70
2.3304
25.90
0.701
0,299
1.864
0.514
12.07
0.722^0334. 7
0.72
2.5844
24.91
0.765
0.235
2.118
0.584
12.90
0.772-23105.1
0.77
2.8385
23.94
0. 827
0.173
2.372
0.654
13.72
0-82125875.5
0.82
3.0924
23.12
0.880
0.120
2.626
0,724
14.46
0.86528643 .9
0.87
3.3464
22.49
0.921
0.07 9
2.880
0.79 4
15,15
0.90631416.2
0.91
3.6004
21.93
0.957
0.04 3
3. 134
0.864
15.73
0.9413^186.6
0.94
3.8544
21.60
0. 978
0.022
3. 388
0.934
16.21
0.S7036957. 1
0.97
4.1084
21 .38
0.992
0.006
3.642
1.004
16.50
0.98739727.4
0.99
4.3624
21.28
0.996
0.002
3.896
1.074
16.65
C. 99642497. 8
1.00
4.6L64
21 .25
1.000
-0.000
4.150
1.144
16.71
1.00045268.2
1.00
182
RUN C<J2974/100374
SPAKWISE PROFILE TH=i
REX =
O.iOOOOE 01
REM
=
6/59.
KEH
=
8861.
XVO =
C.OO CN
DEl2 =
0.619
CM OtH2
0.806 CM
UINF =
16.73 H/S DEL99=
3.62/
CM 0ELT99 =
3,815 CM
Vise =
0.15316E-04 K2/S DELI =
0.9/7
CM UINF
-
16.68 M/S
PORT =
2
' H
=
1.5/9
Vise
= 0.
15179E-
04 M2/S
XLCC =
176.40 CM
CF/2 = O.lOOOOt 01
riNF
=
21.
30 DEG 1
TPLATE =
36.
76 DEG 1
YICMJ
Y/DEL
UlM/ S J
U/UINF
V +
U+
YtCKJ T(DEG Cl
TBAR
TBAR
0. C25
0.007
5.56
C.333
277.4
0.33
O.0546
33.81
0. 191
0.809
0.C28
0.006
5.70
0,341
305 .1
0.34
0.0571
33.57
0.207
0.79 3
0-030
0-008
5.95
0-356
332.8
0.36
0.0597
33.36
0.220
0.780
0.033
0.009
6.18
C.370
360 > 6
0.37
u. 0648
33.10
0.237
0.763
0. 038
0.011
6.55
C.392
416 .0
0 .39
O.0724
32.77
0.258
0.742
0.046
0.013
6.9 8
C.417
499 .2
0.42
O.U825
32.45
0,279
0.721
0. 056
0. 015
7.35
C.440
oiO.2
0.44
0.0952
32.11
0.301
0.699
0.069
0.019
7.72
0.462
, 748 .9.
0.46
0.1105
31.80
0.321
0.679
0. C64
0.023
8,14
0.487
91:?. 3
0.>*9
0.1308
31.52
0. 339
0.66 1
0. 102
0.028
8.38
C.501
1109.4
0.50
0. 1562
31 .26
0-356
0.644
0. 122
0.034
8.64
0.516
1331.3
0.52
0.1867
31 .08
0.368
0.632
0. 147
0.041
8.86
0.530
1608. 7
0.53
0.2222
30,98
0.374
0.626
0.178
0.049
9.10
C.544
1941.5
0.54
0,2629
30.82
0.385
0.615
0-213
0.05 9
9. 29
0.5 55
2j29. 8
0.56
0 .3086
30.80
0.386
0.614
0.254
0.070
9 .43
0.564
277i .6
0.56
0.3oi9
30,80
0. 386
0.614
0. 300
0.083
9.52
C. 569
32/2.8
0.57
0.4254
30.80
0.386
0.614
0.351
0.097
9.59
0.573
3827.6
0.57
0.4889
30.83
0.384
0.616
0.406
0.112
9.63
C.576
4437-8
0.58
0,5524
30.85
0.302
0.6L8
0.467
0. 129
9.62
0.575
5103.4
0-57
0.6159
30.88
0.380
0.620
0. 538
0,148
9.49
0.567
5880 .0
0.57
0.O794
30.85
0.382
0.618 .
0.620
0.L71
9.44
0,565
o7o7 .6
0.56
0. 7429
30.80
0.386
0.614
0.696
0. 192
9.3 9
C.562
7599./
0.56
0.8064
30.70
0. 392
0.608
0.772
0.213
9.41
0.563
8431 . 7
0.56
0.8699
30.59
0.399
0.601
0.848
0.234
9.49
0.567
9263 .8
0.5/
0.9334
30.51
0.405
0.595
0.925
0.255
9.63
C. 57610095. 9
0.58
i . 0604
30.12
0.430
0.570
1.026
0.283
9.86
C.590JL12U5 .3
0.59
1.1874
29.63
0.462
0.53 8
1. 128
0.311
10. 12
0.60612314. a
0.61
1 .3144
29.04
0.500
0.500
1.229
0.339
10.40
0.62213424.2
O.o2
1.4414
28.47
0.537
0.463
1.356
0.374
10.68
0.63814811 .0
0.64
1 . 3o84
27.93
0.571
0.42 9
1.483
0.409
10.98
0.65616197.8
0.66
1.8224
26.81
0.644
0.356
1.610
0.444
11.23
0.67217584.0
0.67
2.0764
25.83
0.707
0.293
1.737
0.479
11.67
0.69718971.4
0. 70
2.3304
24.87
0.769
0.231
1.864
0.514
12.06
0.72U0358.2
0.72
2.5844
23.96
0.828
0.172
2. 118
0.584
12.92
0.77323131.8
0.77
2.8385
23.14
0.861
0«LL9
2.372
0.654
13.75
0 .62225905 .4
0.82
3.0924
22.51
0. 922
0.078
2.626
0. 724
14-53
0. £692 8679.0
0.87
3.3464
21 .98
0.956
0.044 .
2.880
0.794
15.21
0.91031452.6
0.91
3.6004
21.65
0.978
0.02 2
3. 134
0.864
15.83
C. 94634226. 2
0.95
3.8544
21.43
0.991
0.009
3.388
0.934
16.23
C. 97036999. 8
0.97
4.1084
21 .33
0.998
0.002
3.642
1.004
16.53
0.98839773.4
0 .99
4.3624
21.32
0.999
0.00 1
3. 896
1 ,074
16.66
0.99642547 .0
1.00
4.6164
21.30
1.000
-0.000
4.150
1.144
16.72
1.00045320.6
1.00
4.404
L.2L4
16.73
1.00048094.2
L.OO
183
RUM 0S297A/100374
SP^NWISt PROFILfc TH=i t3J
REX
=
O.IOCOQE 01
REM =
blbl.
REH
=
8137.
XVO
U.OO
CK
0EL2 =
0 .So3
CM
0tH2
s
0.740 CM
UINF
=S
16.72
M/S
DEL94=
3. 6di
CM
0ELT99
z
3.802 CM
Vise
=
0.15300E-04
M2/S
deli =
0.di4
CM
UiNF
=
16.69 M/S
PORT
3
H =
i .^4U
Vise
0.15179E-04 M2/S
XLCC
176.40
CM
CF/2 =
O.iJOOOt: ui
TiNF
=
21.30 DEG C
TPL ATE
=
36.71 DEG C
YiCMJ
Y/DEL
U(M/S )
U/UINF
V 4
U4
YICMI
T(DEG C )
TBAR'
TBAR
0.025
0.007
6.43
0,384
277.0
0.38
0.0546
32.98
0.242
0.758
0.028
0.008
6.46
0.386
305 .4
0.59
0.0571
32.66
0.263
0. 737
0.030
0.008
6. 76
C.404
333.2
0.40
0.0597
32.43
0.278
0.722
0.033
0.00 9
6.97
0.417
360.9
0.‘t2
0. 0622
32.28
0.287
0,71 3
0. 038
0.010
7.4 1
G.447
4io . 5
0 .4y
0. 0648
32-07
0.301
0.699
0.046
0.012
7.87
0.471
499.7
0.47
0.0/24
31 .63
0. 329
0.67 1
0. 056
0.015
8.28
0.495
61J.8
O.50
0.0825
31.23
0.356
0.644
0.069
0.019
8.70
0.520
749.6
0.52
0. 0952
30.87
0. 379
0.621
0. C84
0.023
9.02
0.53 9
916 .2
0.54
0. 1308
30.56
0.399
0.601
0. 102
0.028
9.34
C.558
1110.3
0.56
0.1362
30.23
0.420
0.580
0. 122
0.033
9.53
C.570
1332 .6
0.57
0.1867
29.99
0. 436
0.564
0. 147
0. 040
9.75
0.583
iolO.3
0.58
0.2222
29.74
0.452
0.548
0.178
0.048
9.99
0.597
1943 .4
0.60
0.2629
29.58
0-463
0.537
0.213
0.058
10.23
0.612
2332.1
0.61
0.3086
29,23
0.485
0.515
0.254
0,069
10.41
0.622
2776,4
0.62
0.3619
29.15
0.490
0.51 0
0. 300
0.081
10.57
0.632
52 76 . 1
U.05
0.4234
29.05
0.497
0.503
0.351
0.095
10. 70
C.640
5831.4
0.64
0. ‘t-889
28.95
0, 503
0.497
0.406
0. 110
10.85
C.649
4‘»42 .2
0.65
0.5524
28.87
0.508
0.49 2
0.467
0.127
10.9<i
0.654
5108.5
0.65
0.6159
28.82
0.512
0.488
0.538
0.146
10.99
0.657
3aS5 .9
0.66
0,6794
2 8,74
0.517
0.483
0.620
0.168
11.08
0.662
0774.3
0.66
0 . 8064
28.58
0.528
0.472
0.721
0.196
11.11
0.664
7884.8
0.66
0. 9534
28.40
0. 539
0.461
0.848
0.230
11. 17
C. 66 6
92 73.0
0.67
1 • 0604
28.17
0.554
0.446
0.963
0.262
11.25
0.67310522.4
0 • o 7
1. 1874
27.86
0, 574
0.426
1. 102
0.300
11.41
0.68212049.4
0 .68
1.3144
27.55
0.594
0.406
1.229
0.334
11.57
0.69213437 .5
O.o9
1.4414
27.17
0.619
0.381
1. 356
0.369
11.80
0.70614825.7
0.71
1.3684
26.75
0.647
0.353
1.483
0.403
U.9S
0.71716213.9
0. 72
1.8224
25.97
0.697
0.303
1.610
0.438
12.27
0.73417602.1
0.73
2.0 7 64
25.18
0. 748
0.252
1.737
0.472
12-54
C. 75C18990.3
0. 75
2.560%
24.36
0.801
0.199
1.864
0.507
12.84
0.76820378.4
0,77
2. 3844
23-62
0.650
0.15C
2. 118
0.576
13.47
0.80523154.8
0.81
2.6385
22.94
0.894
0.106
2.372
0.645
14.16
0.8472593L.1
0.85
3.0924
22,36
0,931
0.069
2.626
0-714
14.80
0.88528707 .5
0.88
5. 34o4
21.91
0.960
0.04 0
2.880
0.783
15.38
0.92031483.8
0.92
3.6004
21 .62
0.980
0.020
3. 134
0.852
15.87
C. 94934260. 2
0.95
3.8544
21.43
0.991
0.009
3.388
0.921
16.27
0. 97337036. 5
0.9 7
4. 1084
21.33
0.998
0,002
3-642
0.990
16.50
C. 98739812. 9
0.99
4.3624
21,30
1.000
-0.000
3. 896
1.059
16.67
0.99742589.2
i.OO
4.150
1.128
16.69
0 .99845365 .6
1.00
4.404
1.197
16.73
1.00048141.9
1.00
184
RUN 092974/100374
SFANW1SE PROFILE
II
X
14)
REX -
O.IOOOOE 01
REM
5769.
REH
-
8341.
XVO *
0.00 CP
DEL2 =
0.527
CM 0EH2
=
0.758 CM
UINF »
16.74 M/S DEL99=
3.656
CM 0ELT99 «
3.894 CM
Vise =
0.15306E-04 P2/S DELI =
0.736
CM UINF
-
16.71 M/S
PORT *
4
H
=
1.396
Vise
* 0,
1 5178E-
04 M2/S
XLOC *
176.40 CP
CF/2 = O.IOOOOE 01
TINF
=
21.
28 OEG
TPLATE =
36,
65 DEG
Y(CM»
Y/DEL
UCM/S)
U/UINF
y +
U +
Y(CM) T(DEG C)
TBAR
TBAR
0,025
0.007
6.5 4
0.391
277. 9
0.39
0.0546
33.04
0.235
0.765
0.028
0.008
6.85
0.409
305.6
0.41
0.0571
32.75
0. 254
0. 74 6
0.030
0.008
7. 13
0.426
333.4
0.43
0.0597
32.54
0.267
0,733
0.036
0.010
7.55
0.451
389 .0
0.45
0.0622
32.38
0.278
0.722
0. 043
0.012
8.01
0.478
472.4
0.98
0. 0598
32.10
0.296
0.704
0.053
0.015
8.40
0.502
583.5
0.50
0.0724
31.79
0.316
0.6B4
0.066
0.018
8.8 1
0.526
722.4
0.53
0.0823
31.39
0.342
0.658
0.081
0.022
9.16
0.548
889.2
0.55
0.0952
31.01
0.367
0.633
0. 099
0.027
9.4?
C.566
1083.7
0.57
0.ii05
30.65
0. 390
0.61C
0. 119
0.033
9.66
0.577
1305 .9
0.38
0.1308
30.38
0. 408
0.592
0. 145
0.040
9.94
0.593
1583 .8
0.59
0.1302
30.13
0.424
0.576
0. 175
0.048
10.13
0.605
1917,2
0 . oO
0.1867
29.87
0.441
0.559
0.211
0.058
10.38
C.620
2306.3
0.62
0.2222
29-62
0.457
0.543
0.251
0.06 9
10.6 1
0.634
2750,8
0.63
0,2629
29.40
0.472
0.52 8
0.297
0.061
10. 63
C.647
3251,0
0.o5
0.3 085
29.30
0.479
0.52 1
0.348
0.095
11.0 1
0.658
3806 .7
0.66
0.3619 ,
29.05
0. 494
0.506
0.404
0.110
11.17
0.667
49^18.0
0.0/
0 . 92 5 9
28.90
0.504
0,496
0.465
0.127
11.27
0.673
5084.9
0.67
0.4889
26.81
0. 511
0.489
0.536
0.147
11.42
0.682
5862 .9
O.o6
0 .3 329
28.67
0, 519
0.48 1
0.617
0. 169
1L.55
C.690
o 752.0
0.69
0.6159
2 8.54
0.528
0,472
0.719
0. 197
11.65
C.696
7863.3
0./6
0.6799
28.43
0- 535
0.465
0.846
0.231
11.78
C.704
9252. 8
0. 70
U. UU64
28.25
0.547
0.453
0.960
0.263
11.89
0. 71010503. 2
0.71
0. 9339
27.97
0. 565
0.435
1. 138
0.311
12. 1 1
0. 72 312448.2
0. 72
1.0609
27.71
0. 582
0.41 8'
1.354
0.370
12.48
0.74514810.0
0.75
1.1874
27.43
0.600
0,400
1.608
0.440
12.9 1
G. 77ii7586.6
0.77
1.3144
27,15
0.618
0.382
1,862
0.509
13.4 1
C.801203O/.2
0 .60
1.4414
26.82
0.640
0.36 0
2. 116
0.579
13-9?
C.83 423145. 9
0.83
1 • 3689
26.49
0.661
0.33 9
2.370
0.648
14-45
C, 86325924. 5
0.86
1.8224
25.79
0.707
0.293
2.624
0.718
14.99
0.89528703 . i
0.89
2. 0764
25.06
0.754
0.246
2.878
0.787
15.50
0.92631481 • 7
0.93
2.3304
24.34
0. 801
0.199
3. 132
0.857
15.95
C.9523428J ,3
0.93
2.3844
23,65
0,846
0.154
3.386
0.926
16.30
0.9 733 7038. 9
0.97
c.8383
23.02
0.887
0.113
3.640
0.996
16.53
0.98739617 .5
0.99
4.0924
22.49
0. 921
0.079
3. 894
1.065
16.68
0.99642396.2
1.00
3 . 3964
22.03
0.952
0.046
4.148
1 .135
16.75
1 .000^5374 . o
1.00
4.6009
21.70
0. 973
0,02 7
3.854
21 .47
0.988
0.012
9. 108
21.35
0. 996
0.004
9.362
21.32
0,998
0,002
9.616
21.28
1, 000
-0.000
185
RU^ 092974/100374
SP?!NUISE PRUFiLE
TH=i
<5i
REX =
O.IOOOOE 01
REM =
6654.
REH
9920.
XVO =
0.00
CP DEL2 =
0.609
CM 0EH2
0.
902 CM
UINF =
16.73
M/S 0EL99=
3. 605
CM DELT99 =
4.1
072 CM
Vise =
0.15309E-04
M2/S DELI =
0.907
CM UINF
16.
69 M/S
PORT =
5
H =
1.490
Vise
= 0.
1 51 75E
-04 H2/S
XLLC =
176.40
CM CF/2 = O.IOOOOE 01
TINF
21
.25 DEG 1
T PL ATE =
36
.59 DEG (
Y ( C.vj
Y/DEL
U(M/S
) U/LINF Y +
U +
Y(CM) TIDEG C)
TBAR
TBAR
0.025
0.007
6,99
0.418 277.5
0.42
0.0548
34,10
0.L63
0.83 7
0.028
0.007
7.22
0.431 305.3
0.43
0.0571
33,97
0, 171
0.829
0.030
0.008
7.49
C.448 333.0
0.45
0.0597
33.87
0. 177
0.823
0.036
0.009
7.83
0.468 388.5
0.47
0.0622
33.84
0. 179
0.821
0.043
0.01 1
6.13
C.486 471.8
0.49
0.0673
33.76
0. 185
0.815
0.053
0.014
8.30
0.496 582.8
0.50
0.0749
33.82
0. 181
0.819
0.066
0.017
6.44
0.504 721.5
O.bO
O.0851
33.93
0. 173
0.82 7
0.061
0.021
8,49
0.508 888.1
0.51
0.0976
34.08
0. 164
0.836
0. 102
0.027
8.44
C.505 1110. 1
0.50
0.1130
34,32
0. 148
0.852
0. 122
0. 032
8.47
0.506 1332.1
0.51
0.1333
34.58
0.131
0.869
0. 147
0.039
8.60
C.514 1609 ,6
0,51
0.1587
34.77
0. U8
0.882
0. 178
0.04?
8.68
C.519 1942.6
O.5.:
0.1968
34.92
0. 109
0.89 1
0.213
0.056
8.93
0.534 2331.1
0.53
0.2476
34,89
0. Ill
0.889
0.249
0. 065
8.99
0.537 2719.7
0.34
0. 2 V64
34.54
0. 133
0.86 7
0.290
0.076
9,24
0.552 3163.7
0.55
0.3492
34.01
0.168
0.832
0.335
0.088
9.4 3
C.564 3663.2
0.3b
0.4000
33.44
0.205
0.795
0,366
0. lOl
9.61
0.575 4218.3
0.57
0.4509
32,79
0.248
0.752
0.442
0.116
9.81
C.586 4820.8
0,59
0.5010
32.11
0.292
0.708
0.503
0. 132
10. OC
0.59 8 5494.8
0.60
0. 5524
31.61
0.325
0.675
0.579
0.1 52
10.27
0.614 6327.4
0.6i
0 . 6032
31.27
0.347
0.653
0.681
0. 179
10.47
0.626 7437.5
0.63
0.6540
30.68
0.385
0.615
0. 8C8
0,2 12
10.69
C-639 8625, 0
0.64
0.7 046
30.32
0.409
0.591
0.9b0
0.252
10.92
C.6531U490.2
0.65
0. 7556
30.08
0.425
0.575
1. 138
0.299
11.18
0.66812432 .8
0.67
0.8064
29.77
0.^i45
0.555
1.354
0.356
11.54
0.69014791 . 7
0.69
0.6572
29.57
0.457
0.543
1.6C8
0.423
12.08
C.722175ib.d
0.72
O.9080
29.36
0.471
0.529
1.662
0.489
12.64
0 . 75620:i42 . 0
0.76
0.
29.23
0.430
0.520
2.116
0.556
13.25
0.79223117 .2
0.79
i • 0096
29.04
0.493
0.507
2.370
0.623
13.8 1
0.82625692.4
O.dJ
1 * 0604
28.92
0.500
0.500
2.624
0.690
14.40
C-86128667.5
0.66
1.1239
28.77
0. 510
0.490
2. 678
0.756
14,99
0.89631442. /
0.9U
1.1674
28.58
0.522
0.478
3. 132
0.823
15.53
0.92834217.9
0.93
1.3144
28,27
0. 543
0.457
3.386
0.890
15.97
0.95536993.1
0 .93
1.4414
27.87
0. 568
0.43 2
3. 640
0.957
16.36
0.97839768.2
0.98
i.5684
2 7.46
0.595
0,405
3.894
1.023
16,58
0.99142543 .4
0.99
1.8224
26.60
0.652
0.34 8
4. 148
1.090
16.64
C. 99545318, 6
0.99
2.0764
25.76
0.706
0.294
4.402
1.157
16.71
0.99948093 ,8
1.00
2.3304
24.98
0.757
0.243
4. 656
1.224
16, 73
1.00050668.9
1 .00
2.5844
24,24
0.805
0.195
2. 838
23,53
0,851
0.149
3,092
22.87
0. 894
0. 106
3. 346
22.29
0. 932
0.06 8
3.600
21 .86
0. 960
0.04 0
3. 634
21.57
0. 980
0.02 0
^.108
21.38
0.991
0.009
4.362
21 .30
0. 997
0.003
4. 6 io
21.25
1.000
-O.OOC
186
RUN QS2974/100374
SPANWISE PROFILE TH-i (bi
REX
=
O.IOOOOE 01
REM =
6614.
REH
= 9642-
XVO
s
0.00
CP
DEL2 =
0.625
CM
0EH2
= 0.878
CM
UINF
=
16.70
M/S
0EL9=* =
3.666
CM
DEL T99
= 4.034
CM
VI SC
PORT
—
0. l531^E-04
6
H2/S
DELI =
H *
i.216
1.947
CM
UINF
Vise
= 16.67 M/S
» 0.15184E-04 M2/S
XLOC
=
176.40
CM
CF/2 =
O.IOOOOE 01
TINF
TPLATE
= 21.35
= 36.55
DEG (
DEG 1
Y( CM)
Y/DEL
U(M/S)
U/UINF
Y +
U +
YICM)
UDEG c»
TBAR
TBAR
0.C25
0.007
0.00
0.000
277 .0
o.uo
0.0546
35.80
0.049
0.951
0.C84
0.022
o.oc
C.OOO
914.3
0.00
J • 06 7 3
35.67
0.058
0.942
0. 147
0.038
0.00
0,000
loUo . 9
0 .uO
0. U800
35.67
0. 058
0.942
0. 173
0-045
o.oc
C.OOO
1683 .9
0.00
0,0927
35.72
0.055
0-945
0. 198
0.051
o.oc
C.OOO
2161 .0
O.oO
0 . 1 054
35.77
0.052
0.948
0.211
0.055
0.00
C.OOO
il299 .5
0.00
0.1181
35.78
0.051
0.949
0.224
0,056
1.7C
C. 10 1
2*^36, 0
0.10
J. 1308
35.83
0.047
0.953
0.236
0.06 1
2.82
0.169
26 7o . 6
0.17
0. 1435
35.87
0.045
0.955
0.249
0.064
3.69
C.22 1
2713. 1
0.22
0. 1562
35.93
0.041
0.959
0.262
0.068
4.55
0.273
2653 . 6
0.2 7
0. 1689
35.99
0.037
0.963
0.274
0.071
5,20
C.311
29 92.1
0.31
0. 1943
36.12
0.028
0.972
0.287
0.07 4
5.9 1
0.354
3130.7
0.35
0.2197
36.30
0,017
0.983
0.300
0.078
6.48
C. 388
3269.2
0.39
0.2451
36.46
0. 006
0.994
0.312
0.081
6.98
0.418
3407.7
0.42
0. 2 705
36,58
-0. C02
1.002
0. 325
C. 084
7.45
C .446
33*4-3 . 2
0,45
0. 2959
36,6 7
-0. 008
1.008
0.338
0.087
7.85
C.470
3oo4 . 7
0 .47
0. 346 7
36,76
-0. 014
1.014
0. 358
C.093
8.30
C.497
3':/06 •<»
0.50
0.3975
36,68
-0.008
1,008
0.3B9
O.lOl
8.70
0.521
4236. 8
0.52
0,4483
36.47
0. 006
0,994
0.429
0.111
9 .02
0.540
4662 .1
0.54^
0.4991
36.08
0.031
0.96 9
0.480
0. 124
9.2 1
0. 551
?236.2
0.55
0.5499
35,58
0.064
0.936
0. 54 1
0.140
9.31
C. 55 7
5901-1
0 ,3o
0.OQ07
34.87
0.111
0.889
0,617
0, 16C
9. 33
C.558
6/32 . 3
0.56
0.3515
34.12
0. 160
0.340
0.693
0.179
9.3 3
0.558
7363 .4
0,56
U. 7023
33,36
0. 210
0.790
0. 77C
0. 199
9.33
C. 559
8394 a 6
0. 5o
0, 7531
32.68
0. 255
0.74 5
0.846
0.219
9,40
0,563
9223 . 7
0.56
0.8039
32,12
0.292
0,708
0. 922
0.238
9.48
C . 568 1 JU6o . 9
0.5/
0.8547
31.58
0. 327
0.673
1.024
0.265
9.62
C,576iil65, 1
0.58
0. 9U55
3 1.08
0. 360
0.64 C
1. 100
0.284
9.71
C .531119vt,.2
0.56
0 . 93u3
30.77
0. 381
0.619
1. U6
0.3 04
9.87
0. 591 l2o2 7
0. 59
L.O071
30.46
0.401
0.599
1.278
0.330
10 .02
C . 6001^93 3 .o
0 .60
1 . 0579
30,20
0.4L6
0.582
1.405
0.363
10.29
0 .61615^20. o
0.62
1.1087
30.02
0.430
0.570
1.557
0.403
10.66
0.63810963 .1
0.64
1. t595
29.8 1
0.444
0.55 6
1. 709
0,442
11.08
C . 6631 6645 . 4
0.66
1.2357
29.60
0.458
0.542
1.913
0.495
11.61
G .69520661 .8
U.70
1. 3119
29.37
0.473
0.527
2. 141
0.554
12.30
0,73723335.2
0.74
1.4389
29.02
0.495
0.505
2.395
0,620
13,06
0.78220125,7
0.78
1. 5659
28.58
0. 524
C.476
2,649
0.685
13.80
C.82 626896.2
0.83
i.a929
28.14
0.553
0,44 7
2.903
0,75 1
14.5 1
C. 86931066. 7
0. 6 7
1.8199
27.63
0.587
0.413
3. 157
0.817
15. l£
0.90939437 .2
0.91
.i. 0 /39
26.66
0. 650
0.350
3.411
0.882
15. 76
0.94437207.6
0,94
2.3279
25.71
0. 713
0.287
3.665
0,946
16.2 1
0.97139976.1
0.97
4::. 5819
24.85
0,770
0.23 0
3.919
1.014
16.5 1
0.98842/46, 6
0.99
2.0359
24 .05
0.823
0.177
4.173
1.079
16.6 7
0,998453 19. 1
1 .Ou
3.0899
23.29
0.873
O.U 7
4. 42 7
1.145
16. 7 1
1, C0046269.6
1.00
3.3439
22,63
0.916
0,084
3.596
22,08
0. 952
C.048
3.652
21 .70
0. 977
0.023
4.106
21.45
0. 993
0.007
4 . 5 OU
21 .35
l.OOO
-O.OOC
187
RUN 092974/IC0374 SPANWISt PROFILE TH=l (7i
REX «
O.IOGOOE 01
REM =
7 734.
REH
= ■
10138.
XVO *
0.00 CM
DEL2 =
0.699
CM 0EH2
3
0.
917 CM
UINF -
16.77 M/S DEL99=
3.954
CM DfcLT99 =
4.
089 CM
Vise *
0.15158E-04 M2/S DElI =
1.136
CM UINF
-
16.
78 M/S
PORT «
7
H
=
1 .623
Vise
= 0.
15171E
-04 M2/S
XL pc «
176.40 CM
CF/2 = 0.,
LOOOOE 01
TINF
-
21
.20 DEG 1
TPLATE =
36
.74 DEG (
Y(CM)
y/DEL
U(M/S)
U/UNF
7 +
U+
YICMI TIDEG C)
TBAR
TBAR
d. 025
0.006
6.32
C.377
281.0
0 .JO
0.0546
34.13
0. 168
0.832
b.02ti
0.0Q7
6.32
C.377
309. 1
0.38
0. 0571
34.07
0, 172
0.828
0.030
0.008
6.35
0.379
33 7.1
0.38
0. 059 7
34.00
0.176
0.824
0.036
0.009
6.76
0.405
393.3
O.'tO
0. J622
33.83
0.188
0.812
0.093
0.011
7,26
0.433
477,6
0.43
0. 06 73
33.63
0.200
o.eoo
0.053
0.013
7,53
C.449
590.0
0.4D
0.0698
33.57
0.204
0.796
0.066
0.017
7.64
0,455
730.5
0.46
0.0775
33.50
0.209
0.791
0.081
0.021
7.55
C.450
o99 .1
0.^6
0. 0876
33.49
0. 210
0.79C
0.i02
0.026
7.43
C.443
1123.8
0.44
0. 1003
33.63
0,200
0.800
0.122
0.031
7.36
0 .439
i:»48.6
0.44
0.1156
33.81
0. 189
0.81 1
0.147
0.037
7.38
C.440
1629.6
0.44
0.1359
34.04
0, 174
0.826
0.178
0.045
7.56
0.451
1966.7
0.45
u.lol3
34.26
0. 160
0. 84G
0.213
0.054
7.9 1
0.472
2360. 0
0.47
0.1994
34.62
0. 137
0.863
0.249
0.063
8.30
0.49 5
2753.4
0.50
0.2502
34.78
0. 127
0.873
0.290
0.073
8.63
C.515
3202.9
0.51
0.3010
34,86
0.122
0.878
0.335
0.085
8.9 1
0.531
3708.6
0.53
0. 3518
34.61
0.137
0.863
0.386
0.09 8
9.04
0.539
4270.6
0.5‘*
0.4026
34.30
0. 157
0.843
0.442
0.112
9.12
0.544
4888.7
0.54
0. 4634
33.85
0. 186
0.81 4
0.503
0.127
9.16
0.546
5563.0
0.55
0.5042
33.41
0.214
0. 786
0.579
0.146
9.15
C. 646
6405,8
0.55
0.5550
32 .94
0,245
0.755
0.661
0.172
9.22
C.550
7529.7
0.55
0.6058
32.39
0.280
0.72 0
0.808
0.204
9,36
0.559
8934.5
0. 56
U. a666
31.94
0.309
0.691
0.960
0.243
9i53
0.56810620.2
0.57
0.7074
31.60
0.331
0.669
1. 138
0.288
9.71
0. 57912586.9
0.56
0.7582
31.22
0.355
0.645
1.354
0.342
10.00
0.59614975.1
0.60
Q. 8090
30.90
0.376
0.624
1.608
0.407
10.59
0. 63117784.6
0.63
0.8698
30 .62
0-394
0.606
1.862
0.471
11.26
0.67220594.2
0.67
0. 9106
30,41
0.407
0.593 .
2. 116
0.535
12.01
0.71623403.8
0. 72
0.9614
30.25
0,418
0.582
2.370
0.599
12.83
0. 76526213.4
0.7 7
1.0122
30.09
0.428
0,572
2.624
0.664
13.56
0.80929023.0
0.81
1 . Q060
29.96
0.437
0,563
2.878
0.728
14.28
0.85231832.5
0.85
l.l2o5
29.79
0.447
0.553
3.132
0.792
14.99
C. 89434642.1
0.89
1.1900
29.66
0.456
0-544
3; 386
0,856
15.61
0.93137451. 7
0.93
1.31 70
29.30
0.479
0.52 1
3.640
0.920
16.17
0.964^0261 .3
0.9o
1 . 4‘*40
28.98
0. 500
0.50C
3.894
0.985
16.50
0.98443070.9
0.98
1.6/10
26.60
0.524
0.476
4. 148
1.049
16.67
C. 99445660.4
0.99
1.8260
27.65
0.585
0.41 5
4.402
1. 113
16.75
C.99948o90. 0
1.00
2.0/90
26.70
0.646
0.354
4.656
1.177
16.77
1.00051^99.6
i.OO
2.3330
25.73
0. 7C9
0.291
2.58/
24.82
0.767
0.233
2.841
24.02
0.819
0.18 1
3.096
23.21
0. 871
0.129
3.349
22.53
0.915
0.085
6.603
22.01
0.948
0.052
3.857
21.62
0.973
0.027
4.111
21.33
0. 991
0.009
4,365
21 .23
0.998
0.002
4.619
21.20
1. 000
0.000
188
RUN 092S74/ 100374
SPANUISE PRGFU.E
TH»1
(81
hex *
O.IOOOOE 01
REM =
7051.
REH
=
9077.
XVO =
0.00 CM
DEL2 =
0.640
CM DEH2
s
0.823 CM
UINF =
16.74 P/S DEL99=
3.896
CM DEL T99 -
4.022 CM
Vise =
0.15195E-04 M2/S DELI *
0.953
CM UINF
=
16.73 H/S
PORT
8
H
-
1.488
Vise
= 0.
15175E-
04 M2/S
XEOC *
176.40 CP
CF/2 = O.IOOOOE 01
TINF
= •'
21.
25 DEG C
tplate =
36.
76 DEG C
YICM)
Y/DEL
U(M/S>
U/LINF
Y +
U+
Y(CMi T(DEG C)
TBAR
TBAR
0.025
0.007
5.90
0.353
279.8
0.35 .
0.0546
33.71
0,197
0.803
0.028
0.007
5.94
C.355
307.7
0.3 5
0.0571
33.66
0.200
0.800
0.033
0.008
6.32
0.378
363.7
0.38
0.0597
33.36
0.220
0.78C
0.041
0. 010
6.94
0.415
447.6
0.41
0.0622
33.08
0.237
0,763
0.051
0.013
7.56
0.451
559.5
0.45
0.0648
32.92
0.248
0.75 2
0.063
0.016
7.94
C.474
699.4
0.47
0.0673
32. 76
0.258
0.742
0.C79
0.020
8.34
0.498
867.3.
0.50
0.0749
32.37
0.283
0.71 7
0-OS7
0.02 5
8.60
0.514
1063.1
0.51
0.0851
31.96
0.310
0.690
0.117
0.030
6.84
0.528
1287.0
0.53
0.0978
31.60
0.333
0.66 7
0. 142
0. 03 6
9.06
0.541
1566.7
0.54
0.1130
31.24
0.356
Q.644
0. 173
0.044
9.31
C.556
1902 .5
0.56
0. 1333
31.02
0- 371
0,629
0. 208
0.053
9-56
0.571
2294 .1
0-57
0. 1687
30.66
0-394
0.606
0.249
0.064
9.77
0.584
2741.8
0.58
0.1892
30.57
0,399
0.601
0.295
0.076
9.98
0.596
:»245.4
0.60
0.2248
30.25
0.420
0.58C
0-345
0. 08 9
10. 13
C.605
3604 . 9
0.61
0 . 2o03
30.07
0.432
0.568
0.401
0. 103
10.28
C.614
4420.4
0.61
0.3111
29.86
0.445
0.55 5
0.462
0.119
10.3 6
C.619
6091 . 9
0.62
0.3646
29.72
0 . 454
0.546
0.533
0. 137
10.45
0.624
5875 .2
0.62
0.4280
29.56
0.464
0.536
0.615
0.158
10.50
0.627
6770,5
0.63
0.9915
29.46
0-471
0,529
0.716
0. 134
10.58
0.632
7 86 9.6
0.63
0. 5350
29-41
0,474
0.526
0.843
0,216
10.63
G. 635
9288. 4
0.63
0.6185
29.33
0-479
0-52 1
0.958
0.246
10.74
0.64210547.4
0,04
u. 6820
29.23
0.485
0.515
1. 135
0.291
10.88
C.65C1250i .8
0 .66
0.6090
29,09
0.495
0.505
1. 351
0-347
11.20
C. 66914663. 9
0.6 7
0. 9360
28.91
0.506
0.494
1 .605
0.412
11.66
0 .69717661 .6
0. 7u
1 . 0630
28.71
0, 519
0.48 1
1.859
0.477
12.18
0. 72820479.3
0,73
i . 190U
28.47
0.535
0,465
2. 113
0.542
12.75
0-76223277.1
0.76
1 .31 70
28.19
0. 553
0.447
2.367
0.607
13.36
0. 7982o074 • o
0.60
1 . ^*t40
27.88
0.573
0.427
2.621
0.672
13.99
C, 83626872 .3
0.84
1.6710
27.53
0. 595
0.405
2.875
0- 738
14.66
0.87631670.2
0.88
1 .6250
26.79
0.643
0.357
3. 129
0.803
15.23
0.91034467.9
0.91
2.0790
26.02
0.692
0.308
3.383
0. 868
15.79
0.94337265.7
0.94
2.3330
25.18
0.746
0.254
3.637
0.933
16.24
0.970‘#0063.4
0.97
2. 5870
24.43
0.795
0.205
3.891
0.998
16.53
0,96842861.1
0.99
2.8410
23-65
0.845
0.155
4. 145
1.063
16.71
C. 99845636- 8
I. 00
3.0950
23.04
0.685
0.115
4.399
1.129
16.74
1 • CO 04645 6 • o
1.00
3.3990
22.43
0.924
0,076
3.603
21.93
0.956
0.044
6. 65 7
21.57
0.980
C.02C
4.111
21.37
0.993
0.007
4.365
21.28
0.998
0.002
4.619
21-25
1.000
0,000
189
RUN 092S 74/ 100374
SPANWISb PROFILE
TH=1
i9i
REX *
O.IOOOOE 01
REM =
6381.
REH
=
8617-
XVO *
0.00 C«
0EL2 =
0.584
CM DfcH2
0.
782 CM
UINF =
16.78 M/S DEl99=
3.859
CM 0cLT99 =
3.
969 CM
Vise -
0.15365E-04 M2/S DELI =
0.829
CM UINF
=
16.
72 M/S
PORT *
9
H
i.4l9
Vise
«
o
II
15161E
-04 M2/S
XLOC =
176.40 CM
CF/2 = O.IOOOOE 01
TINF
-
21
.32 DEG J
TPLAT6 =
36
.78 OEG (
Y(CM»
Y/OEL
U<M/S)
U/LINF
¥ +
u+
YICMI T(DEG CJ
TBAR
TBAR
0. 02S
0-007
6,51
0.388
277.3
0.39
0.0546
33.47
0.214
0.786
0.028
0.007
6.53
C.389
305.2
0.39
0.0571
33.40
0.219
0.78 1
0.033
0.009
7.01
0.417
360 .7
0.42
0.0597
33.34
0.223
0.777
0.041
0.011
7.56
0.450
443.9
0.45
0.0o22
33.04
0-242
0.758
0.05L
0.013
8.11
0.483
554.9
0.48
0. 0673
32.56
0.273
0.727
0.063
0.016
8.60
0.513
693.7
0.51
0.0749
32.09
0.304
0.696
0.079
0.020
8.95
0.534
860.1
0.53
0. 0851
31.60
0.335
0.665
0. 097
0.025
9.29
0.553
1054.4
0.55
0.0978
31.13
0.366
0.634
0.117
0.030
9.58
0.571
1276.3
0.57
0.1130
30.74
0,391
0,609
0.142
0.037
9.79
0.583
1553.6
0.58
0.1333
30.41
0.412
0.388
0. 173
0.045
10.01
0.597
1886.8
0. 60
0. 1 587
30.16
0.427
0.573
0.208
0.054
10.25
0.611
2275.2
0.61
0.1892
29.89
0.446
0.554
0.249
0. 064
10.43
C.622
2719.2
O.o2
0.2248
29.79
0-452
0.546
0.295
0.076
10.62
0,633
3218.6
0.63
0.2654
29.58
0.466
0.534
0,345
0.090
10.78
0.642
3773.5
0 .64
0.3111
29-48
0-472
0.52 8
0.401
0.104
10.95
0.652
4384.0
0.65
0.3645
29.30
0.484
C.516
0.462
0.120
11.03
0.657
3049.9
0.66
0.4280
29.23
0.486
0.512
0.533
0.138
ll.lO
0.661
3826.8
0.66
0.4915
29.12
0.496
0.504
0.615
0.159
11.21
0.668
6714.7
0.67
0.5550
29.02
0. 502
0.498
0.716
0.186
11.25
C.670
7824.5
0.67
0.5185
28.94
0.507
0.493
0. 843
0.219
11.37
0.678
9211 .9
0 .o8
0. 6820
28.87
0.512
0.486
0.958
0.248
11.52
0.68610460.4
0,69
0.7455
28-76
0. 519
0.48 L
1.097
0-284
11.67
0.69511986.5
0.70
O.8090
28.66
0. 525
0.475
1.224
0.317
11.82
0.70413373.8
0.70
0.8/25
28.56
0.532
0,46 8
1.35L
0,350
11.96
0.71414761,2
O./l
0.9360
28.49
0.536
0.464
1.478
0-383
12.22
C. 728 16148.5
0.73
1.0630
28-22
0.554
0.446
1.605
0.416
12.44
0.74117535. a
0.74
1. 1900
27.89
0.575
0.425
1. 732
0.449
12.67
C. 75518923.1
0.76
1,3170
27.56
0. 596
0.404
1.859
0.482
12.96
0.77220310.5
0.7 7
1.4440
27.25
0.616
0.384
2.113
0.548
13.43
0,80023085 .1
0.80
1.5710
26,89
0. 640
0.36C
2.367
0.613
13.98
C. 83325a59.8
0.83
1.6250
26.15
0.687
0.313
2.621
0.679
14.51
0.86528634.4
0.86
2.0790
25.41
0. 735
0.265
2.875
0.745
15.08
0.89831409.1
0.90
i.3330
24.67
0-783
0.21 7
3. 129
0.811
15.57
0.92834183.7
0.93
2.5870
24.00
0.02 7
0.173
3.383
0-877
16.03
0.95536958.4
0-95
2.8410
23.32
0.871
0.129
3.637
0.942
16.36
C .97639733 .0
0.98
3. 0950
22.71
0.910
0.09 0
3. 891
1.008
16.62
0.99042507.7
0.99
3.3490
22.23
0.941
0.05 9
4. 145
1.074
16,74
0.99745282. 3
1.00
3. 6030
21 .85
0.966
0.034
4.399
1.140
16.78
1.00048057.0
1.00
3.8570
21.55
0.985
0.015
4.653
1. 206
16. 79
1.C0050831. ?
i.OO
4.11IQ
21.42
0.994
0.006
4.365
21.33
0.999
0.00 1
4.619
21 .32
1.000
-0.000
190
RUN 092974/100374
SFANWiSt profile TH=a (iOJ
REX -
O.IOOOQE 01
REW
I =
6720.
REH
=
9158.
XVO *
0.00 CM
0EL2 =
0.O12
CM DEH2
0.832 CM
UINF ^
16.72 P/S
DEL99=
3.831
CM 0tLT99 =
3,944 CM
Vise =
0.15224E-04 M2/S DELI =
0.908
CM UINF
=
16.71 M/S
PORT =
10
H
=
1.483
Vise
= 0.
15175E-
04 M2/S
XLCC -
176.40 CP
CF/2 = 0.:
LOOOOt 01
TINF
21.
25 DEG 1
TPLATE =
36.
80 OEG 1
Y(CMJ
Y/D.EL
UtP/S ) U/UINF
Y +
U +
Y(CMi T(DEG C)
TBAR
TBAR
0. 025
0.007
6.16
0.366
2 79.0
0,3 7
0. 0546
34.05
0. 177
0.823
0.C2 8
0.007
6.3 1
C.377
306 ,9
0.38
0.0571
33.97
0,182
0.81 8
0.033
0.009
6. 78
C.40 5
3b2 . 6
0.4 1
0.0597
33.74
0. 197
0.80 3
0.04L
0.01 1
7.32
0.438
446.3
0.44
0,0622
33.50
0.212
0.788
0.051
0.013
7. 82
C.468
557.9
0.4 7
0.06/3
33.13
0. 236
0.764
0.063
0.017
0.23
0.492
697.4
0.49
0.0749
32.74
0.261
0.73 9
0.079
0.021
8.63
C. 516
664.8
0-32
0 . J851
32.33
0.288
0.712
0.097
0.025
9.0 1
Q. 539
lOoO • 1
0.54
0 * 09 78
31.97
0.311
0.689
0. 11 7
0.03 C
9 . 2 c
C.550
1^83 . 2
0*33
0.1130
31,60
0.335
0.665
0.192
C. 03 J
9.49
0.567
1562 • 2
0.5 7
0. L:>33
31.30
0.353
0.647
0. 173
0.045
9.6 9
C .580
i u9o .9
0.58
0. 158 7
31.03
0.371
0.629
0.208
0.054
9.90
0. 69 2
2<i.3 / ■ 5
0.59
0, 1892
30.88
0.38L
0.619
0.249
0.06 5
10.02
C.59 9
2733.8
0 .60
0. 2248
30,77
0.388
0.612
0.295
0. 07 7
10. 13
0. fcC6
36.0
U.6i
0. 2654
30.65
0.396
0.604
0.345
0.090
10.20
C .6 10
3 7 93 . 9
0 *0 i
0.3111
30.59
0.400
0.600
0.401
0.105
10.23
C.612
440 7.0
0.6 1
0.3o43
30,59
0.400
0.600
0.462
0.121
10.23
0.612
5077.1
0.6 1
0. 4280
30.57
0.401
0.599
0.533
0. 139
10.25
G.613
o85o . 2
0.6l
0. 4913
30.55
0.402
0.598
0.615
0.160
10.25
C . 6 1 3
o7 50 . 9
0.61
0.5350
30.55
0.402
0.598
0.691
Q.160
10.28
0.615
7387 . 8
0.6i
0. 6l83
30.54
0.403
0.59 7
0.767
0.20 0
10.36
C.620
8424,6
0.62
0.6820
30.39
0.412
0.588
0. 643
0.22 0
10. H 1
0.623
9261 .3
0.62
0.7453
30.39
0.412
0.588
0.919
0. 240
10.49
C .62710090. •»
0.63
O.809O
30.06
0.433
0.567
1.021
0.267
10. 7C
0 . 640 11^14.3
0.64
0.8 725
30.10
0.431
0.569
UC97
0.286
10. 8 1
C» 6461^051 • 1
0.63
0.9360
29.92
0.443
0.557
1.224
0.32 0
1 1 . 1 C
0 .664 i j'44t> . 9
0.66
1 .0630
29.49
0.470
0.53 0
1.351
0.353
11.38
0.631 l'»o40 . 8
0.6 6
1 . 1900
29.02
0.500
0.500
1.478
0.386
11.62
0 . 6951623a .6
0.70
1.31 70
28.56
0.530
0.470
1.605
0.419
1 1 .88
C ■ 7 1 0 1 7 oou • 4
0.71
1.4440
27.99
0.567
0.433
1.732
0.452
12. 18
C, 72819025. 2
0.73
1.5710
27.55
0.595
0.405
1.659
0.485
12.52
C. 7492O420-O
0,73
1.8250
26.56
0.658
0.342
2. 113
0.552
13.19
C .73923209 . 0
0.79
2.0790
2 5.64
0.718
0.282
2.367
0.618
13.83
0.82725999.2
0 .83
ii.3330
24.79
0-773
0.227
2.621
0.684
14.45
C. £642
u78o • 0
0. 86
^.3870
24.00
0.823
0.177
2.875
0.750
15.01
C. 89831578. 4
0.9U
2 * 84 10
23.24
0.872
0.12 8
3. 129
0. 81 7
15.35
C • 91834308. 0
0.92
3.0950
22.61
0.913
0.087
3.383
0.883
16.00
0.957371D/ .7
0.96
3.3490
22.11
0,945
0.05 5
3.637
0,949
16.33
C. 97709947, 3
0.98
3.6030
21.73
0.969
0.03 1
3.89 1
1.016
16.56
0 .99042/36. 9
0.99
3.O570
21 ,47
0.986
0.014
3.891
L.016
16.56
0. 99042706. 9
0.99
4.1110
21.32
0.996
0.004
4. 145
1.082
16.7 0
C. 99945526. 5
i .00
4. 3650
21.25
1.000
-0.000
4. 399
1.148
16.72
1 ■ 00 0460 l6 . 1
i.OO
191
RUN 0S2974/100374 SPANWISt PROFILE TH=i (iU
REX
=
O.IOOOOE 01
REM =
7255.
REH
= 9490.
xvc
-
0.00
DEL2 =
0.659
CM
0EH2
= 0.862
CM
UINF
=
16.72
N/S
0EL99=
3.907
CM
0ELT99
» 3.987
CM
Vise
=
0.l5196E-0^
K2/S
OELl =
1.099
CM
UINF
16.72 1
M/S
PORT
=
U
H =
1 .667
Vise
= 0.15178E-04
M2/S
XLCC
176.40
C^‘
CF/2 =
O.IOOOOE 01
TINF
= 21.28
DEG C
TPLATE
= 36.80
DEC C
Y(CM)
Y/DEL
U(M/SI
U/UINF
7 +
U +
YICMi
TIDEG Cl
TBAR
TBAR
0.C2 5
0.007
4.94
0.296
279 .4
0.30
0.0546
35,21
0.103
0.897
0. 030
0.008
4.9 7
C.297
335-3
0.30
0.0571
35.17
0.105
0.895
0.033
0.008
5,14
C.308
363.3
0.31
0.0597
35.16
0. 106
0.894
0.C36
0.009
5.51
0 . 32 9
391 ,2
0.33
0.0622
35-12
0. 108
0.89 2
0.043
0.011
5.95
C.356
475.1
0.36
0.0646
34.98
0. 117
0.883
0. 053
0.014
6.34
0.379
586.6
0.56
0.0673
34.82
0. 126
0.872
0.066
0.017
6.75
C.404
726.6
0.40
0.0724
34,56
0.145
0.855
0. C8l
0.021
7.11
0.425
694 .2
0.43
0.0800
34.28
0. 162
0.83 8
0.099
0.025
7.34
C.439
1069.6
0.44
0.0902
33.99
0. 181
0.819
0.119
0.031
7.59
0.454
1313.4
0.45
0.1029
33.73
0. 198
0.802
0. 145
0. 03 7
7.85
C.470
1592.9
0.47
0.1161
33.47
0.215
0.785
0. 175
0.045
8.0?
0.483
1928 .2
0.46
0.1364
33.19
0.232
0.768
0.211
0.054
8.22
C.492
2319.4
0.49
0.1636
32.98
0.246
0.754
0.251
0.064
8.34
0.499
2766.5
0.50
0.1943
32.77
0.260
0.740
0.297
0,076
8-45
C.506
32o9 . 5
0.51
0.2299
32.67
0.266
0.734
0.34b
0.089
6.44
0,50 5
3828. 4
0.51
0.2705
32.54
0.274
0.726
0.4 04
0.103
8-46
C.506
4443 .2
0.5.1
0.3162
32.53
0.275
0.72 5
0.465
0.119
8.4C
0.503
5113. 9
0.50
0-3696
32.49
0.278
0,722
0.536
0.137
8.36
C.500
5696,3
0.50
0.‘*^331
32.48
0.279
0.721
0.617
0.158
8.33
0.498
6790.6
0.50
0.4966
32.48
0.279
0.721
0.693
0.177
8 .32
C .49 8
7026 .9
0.50
0.5601
32-51
0.276
0.724
0. 770
0.197
8.42
0. 504
8407.3
0.5 0
0.6236
32.41
0.283
0.717
0.846
0.216
8.56
0.512
9305.6
0.51
0.6671
32.33
0,288
0.712
0. 922
0.236
8. 77
C. 52510144.0
0.52
0.7506
32.30
0. 290
0.710
1.024
0.262
9.11
0.54511261 . 7
0.55
0.6141
32.17
0.298
0.702
1. 125
0.286
9.56
0.57212379,5
0.57
0.6776
32.04
0.307
0.693
1.22 7
0.314
9,92
0.59313497.3
0.59
0.9411
31.76
0.325
0.675
1.3 54
0.346
10.31
0 .61714694.6
O.o2
1.0661
31.26
0.357
0.643
1.481
0. 379
10.69
C. 63916291. 8
0.64
1.1951
30.64
0.397
0.603
1.608
0.41 1
11.03
0.65917689.0
0.66
1.3221
29.92
0.444
0.556
1. 735
0.444
11.39
C. 631 190 80. 3
0.66
1.4491
29.20
0.490
0.510
1.862
0.477
12.04
C-720204B3 .5
0.72
1.5761
28-55
0. 532
0.46 8
2. 116
0.542
12.56
0.751252 76.0
0. 75
1.6301
27.27
0.614
0.386
2.370
0.607
13.34
0. 79 320072 .5
0.60
2.0641
26.19
0.684
0.316
2. 624
0.672
14. 1 1
C, 8442 66 0 7 .0
0.64
2.3361
25.19
0.749
0.251
2.878
0.737
14.78
0,8 6431001 . 4
0.66
2.5921
24,26
0. 808
0.192
3. 132
0.802
15.40
0.9213^455.9
0,92
2.6>*6i
23.47
0.859
0.141
3.386
0.867
15.87
C, 94937250. 4
0.95
3. 1001
22.74
0.906
0.094
3.640
0.932
16.26
0 ,9734U04‘t .9
0.9 7
3.3541
22.25
0.938
0.06 2
3.894
0.997
16.51
C.98742o39,4
0.99
3.6061
21.78
0.968
0.032
l40
1.062
16.65
C. 99645033. 6
1 .OO
5.6621
21.53
0.984
0.016
4.402
1,127
16.72
1.00046426.3
l.OO
4.1161
21 .38
0.994
0.006
4.370
21 .30
0.999
0.001
4. o24
21.28
1.000
0.000
192
SPANWISt AVEkAGt UF 1 1 Z STAllij^4S
YJCM)
U(H/S1
U/UlNr
noi
TEAR
TBAR
0.055
6. 77
0.4U‘»
34. O'*
0, 174
0.B26
0.057
6.83
0.406
33.90
0.183
0.817
0.060
6«89
0.412
33. 73
0. 194
0.806
0.065
7.01
0.419
33.42
0. 214
0.706
0,072
7,. 16
0.«t26
33. 12
0.234
0.766
0.083
7.33
0.438
32.82
0.253
0.747
0.095
7.48
0.447
32. 57
0.269
0.731
O.llO
7.61
0.<»55
32.36
0.283
0.717
0.131
7-77
0.464
32. 19
0.293
0.707
0.156
7.94
0.474
32. 03
0.304
0.696
0.187
8. 12
0.485
31.93
0.310
0.690
0.222
8.50
0.508
31.84
0.316
0.684
0.263
9.0/
Q. 542
31.74
0.322
0.678
0.309
9.51
0. 568
31.66
0. 326
0.672
0.362
9.62
0.587
31. 34
0.336
0.664
0.425
9.99
0.597
31.38
0. 346
0.654
0.489
10.07
0.602
31.19
0.358
0.642
0.552
10.12
0.606
31. JO
0.371
0.629
0.6 16
10.15
0. 607
30. 76
0. 386
0.614
0.679
10. 16
0 .o08
30.49
0.404
0, 596
0.743
10.22
0.611
30.27
0.418
0.582
0.806
10.28
0.614
30.03
0.434
0.566
0.87C
10.35
u. oio
29,63
0. 446
0.554
0.933
10.^3
0. 623
2y. 64
0.459
0.541
1.060
10.63
0.635
29.27
0.482
0.518
1. 187
1 0. 66
0. o'»9
2 6 ■ 8^
0. 507
0.49 3
1.314
11.10
0 . 663
28. 30
0.533
0. 467
1.441
11.35
0.679
26.07
0.560
0.440
1.568
11.62
0. 694
2/. 84
0.588
0.412
1.822
12.24
0. 731
26. 76
0. 646
0. 354
2.076
12. vu
0. 7 71
25 • 88
0. 703
0.297
2.330
13.:»7
0.811
25.01
0. 759
0.241
2.564
1 4.c3
0. 630
24. 21
0. 811
0. 189
2.838
14. 86
0. 888
23.45
0. 860
0.140
3 .092
15. ‘♦1
0.9<:1
22 . 80
0.902
0.098
3. 346
15.92
0. 95^:
22.25
0.937
0.063
3.600
16.30
0. 9 74
21.63
0. 965
0.035
3.854
16.35
0.989
21. 33
0. 984
0,016
4. ice
16«6o
0.997
21.37
0. 994
0.006
4.362
16. 73
1.000
21.30
0.999
0.001
4.616
16.73
1.000
21.28
L.OOO
0.000
AVG LINF
= 16.73 M/
S
VibC = 0.1527jt-04
M/S
AVG REM
= 6792.
AVG
BEH = 9200.
A V5
rt= 1.54
AVG TC =
36.72 DEG
c
193
RUN OS2574/100274
SP^NWISE PKOFILE
TH=0
UJ
. . /
■ / ■
REX »
O.IOOOOE 01
REM =
6833.
REH
3898. . /
XVO =
0.00 C^^
DEL2 =
0.626
CM 0EH2
0.
356 CM
UINF =
16.71 M/S 06L99=
CM 0tLT99 =
3.
76 8 CM.
Vise -
0.15323E-04 R2/S DELi =
1.048
CM UINF
=
16.
70 ^/S
PORT =
1
H
-
l.o72
Vise
II
o
•
15253E
-04 M2/S
XLGC =
176,40 CM
CF/2 = O.iOQOOE 01
TINF
ss
22
. 14 DEG (
TPLATE =
36
.17 OE6 (
YICMJ
Y/OEL
UIM/S)
U/UINF
¥ +
U +
V(CM) T(DEG C)
T8AR
TBAR
0.025
0.007
4.86
0.291
277.0
0.29
0.054O
31.79
0.312
0.688
0.026
0.008
5.00
0.299
304.7
0.30
0. 0571
31.60
0.326
0.674
0.030
0.008
5.22
0.312
332 . 4
0.31
0.0597
31.21
0.354
0.646
0.033
0.009
5.42
0.324
3o J .2
0.32
0. 0648
30.65
0.393
0.607
0.038
G.OLC
5.73
0,343
415,6
0.34
0.0/24
30.04
0.437
0.563
0. 046
0.013
6.14
0.367
498.7
0.37
0 • 0825
29.35
0.486
0.514
0. G56
0.015
6.49
C.388
b09 . 5
0.39
0. 0952
28.81
0.524
0.476
0.069
0,019
6 .80
0.407
740 .0
0.41
0. il05
28.28
0.563
0.437
0. CB4
C. 023
7. 13
0.427
914.2
0.43
0. 1308
27.87
0.592
0.408
0. 102
0.028
7. 40
G.442
1108.2
0.44
0.1562
27.46
0.621
0.379
0. 122
0.034
7.6 3
0.456
1329. 8
0.46
0. loo7
27.08
0.648
0.352
0. 147
0.041
7.86
C.470
l60o . 6
0.4 7
0.2222
26.62
0.666
0.334
0. 178
0.049
6.08
0.484
1939 . 3
0.48
0. 2629
26,56
0.665
0.315
0.213
0.059
8.24
C.493
232 /. 1
0.4 9
O.308O
26.35
0.700
0.300
0.254
0.070
8.37
0.501
2770.4
0.50
0. 36i9
26.20
0.711
0.289
0. 300
0.083
8.4 5
C.505
5269.1
0.5 1
0. 42 54
26.02
0.723
0.277
0.351
0.097
8.47
0.50 7
io2 3 . 1
0 . 5 1
0.4889
25.91
0.732
0.266
0.406
0.112
8.47
0.507
44 j2 • 6
0.51
0.5524
25.82
0. 737
0.26 3
0.46 7
0.129
8,44
0. 505
3097 ,5
0.51
0.6159
25.71
0. 745
0.255
0. 538
0. 148
8.4 1
0.503
58 73 .2
0.50
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25.61
0. 752
0.248
0.620
0.171
6,36
0. 50 0
6759.8
0.50
0. 8064
25.45
0. 764
0.236
0.696
0. 192
8.41
C.503
7590 .9
0.50
1 ■ 0^04
25,13
0. 787
0.213
0.772
0,213
8.46
C.508
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0.51
1.18/4
24.98
0.797
0.203
0.846
0.234
0 .6 8
0.519
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1.3144
24.85
0.807
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0.53
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24,73
0.815
0.185
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0.283
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0.55
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0.824
0.176
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0.311
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C. 57812300. 5
0.5 8
1.8224
24.35
0, 843
0.157
1.229
0.339
10.08
0,6031 34 Jd . 7
0 .60
4.0/64
24.06
0- 063
0.137
1.356
0.374
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23.73
0.887
0.113
1.483
0.409
10.92
0.653lol79. 1
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2 . 5844
23.44
0.907
0.093
1. 610
0.444
11. 26
C • 6741 75o4 • 3
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2.8385
23.11
0.931
0.06 9
1.737
0.479
11.65
0,697 18949 • 5
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3 • 0924 ,
22.82
0.951
0.049
I. 864
0.514
12.07
0.72220334.7
0.72
3 . 3464
22.59
0.968
0,032
2. 118
0.584
12.90
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0.983
0.017
2.372
0.654
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22.24
0,993
0.007
2.626
0. 724
14.46
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0.8 7
4. 1004
22.17
0.998
0.002
2.880
0. 794
15.15
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0.91
4. 3044
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3. 134
0. 364
15. 73
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3.642
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C .98739727 .4
0,99
3.896
1 .074
16,65
C .99642497 .o
1.00
4. 150
1. 144
16.71
1 .00045263 .2
1.00
194
RUN 0S2974/10027A
SP/INWISE PHOFlLt
TH=0
REX «
O.ICOOOE 01
REM =
6 759.
REH
3924-
XVO ' *
o.oa CM
DEl2 =
0.619
CM 0EH2
0.358 CM
UINF =
16.73 M/S DEL99*
3.627
CM 0ELT99 =
3.763 CM
Vise *
0.153166-04 M2/S DEL! =
0.977
CM UINF
=
16-72 M/S
PORT =
2
H
=
1,5 79
Vise
= 0,
15262E-
04 M2/S
XLOC =
176.40 CM
CF/2 = O.IOOOOE 01
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=
22 .
24 DEG
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36.
23 DEG 1
Y4CM)
Y/DEt
UCM/S)
U/UINF
74
U+
YICM) TIOEG C)
TBAR
TBAR
0.025
0.007
5.58
C.333
^77. 4
0 . j 3
0. 0546
31.66
0.327
0.673
0.028
0.006
5.70
0.341
305.1
0.34
0.0571
31.40
0.345
0.65 5
0.030
0.008
5.95
C.356
332.8
0.36
0.0597
31.07
0.369
0.631
0.033
0*009
6.16
0.370
360 .6
0.37
0.0648
30.45
0.413
0.587
0.038
0.011
6.55
C.392
416.0
0.39
0.0724
29.84
0.457
0.543
0.046
0.013
6.98
0-417
499 .2
0.42
0.0825
29.18
0.503
0.497
0. 056
0.015
7.35
C.440
610.2
0.44
0.0952
28.60
0.545
0.455
0.069
0.019
7.72
C.462
748.9
0.46
0.1105
28.04
0.585
0-415
0. C84
0.023
8.14
0.487
915 .3
0.49
0. 1308
27,58
0,618
0.382
0. 102
0.02 8
8.38
C.501
1109.4
0,50
0.1562
27.16
0.648
0.352
0. 122
0,034
8.64
C.516
1331 .3
0.52
0.1867
26.80
0.674
0.326
0. 147
0.041
8.86
C.530
1608. 7
0.53
0.2222
26.55
0.691
0.309
0.176
0.049
9.10
0 .544
194i ,5
0.54
0.2629
26.32
0. 708
0.292
0.213
0.059
9.29
C-555
2329.8
0.56
0.3886
26.10
0.724
0.276
0.25^
0.070
9.43
0,564
27 73 ■ 6
0.56
0.3619
25.95
0.735
0.265
0.30C
0. 083
9.52
C.569
32 72 .8
0.57
0.4254
25.78
0.746
0.254
0.351
0.097
9.59
0.573
3827 .6
0.57
0.4889
25,67
0.755
0.245
0.406
0.112
9.63
C.576
4437-8
0*58
0.5524
25.57
0. 762
0.236
0.467
0. 129
9.62
0,575
5103.4
0.57
0.6159
25.49
0.767
0.233
0.538
0.148
9.49
0 .567
588J .0
6.57
0.6794
25.41
0.773
0,227
0.620
0. 171
9.44
C.565
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25.26
0. 784
0.216
0.696
0.192
9,39
0.562
7599 . 7
0.56
0,9334
25.18
0.790
0.210
0.772
0.213
9.4 1
C. 56 3
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0.5o
1 .0604
25.06
0-798
0.202
0.848
0.234
9.49
0.567
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24.95
0.806
0.194
0.925
0.255
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C. 5 7610093 .9
0.5 6
1.3144
24.86
0.812
0. 186
1.026
0.283
9.86
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0.59
1 . 4414
24.76
0. 819
0.181
1. 128
0.311
10.13
C. 60612314. 8
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1 • 5684
24.65
0. 828
0.172
1.229
0.339
10. 4C
C. 62213424. 2
0.62
1.8224
24.41
0.845
0.155
1.356
0.374
10.68
0.63814^11 .0
0 .64
2.0764
24.09
0.867
0.L33
1.483
0.409
10-98
0.65616197.8
0.66
2.3304
23.79
0,889
O.U 1
1.610
0.444
11.23
0-672 17584 .6
0.67
2.5844
23.49
0.910
0.090
1.737
0.479
11.67
€.69718971 .4
0. 70
2.8385
23.19
0.932
0.068
1.864
0.514
12.06
0.72120358.2
0.72
3.0924
22.92
0.951
0.049
2. 118
0.584
12.92
0.77323131.8
0-77
3.3464
22.67
0.969
0.031
2.372
0.654
13.75
C. 82223905. 4
0. 62
5. 6004
22.47
0.983
0.017
2.626
0.724
14.53
C. E6928679.0
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3. 8544
22 .34
0.993
0-007
2.880
0.794
15.2 1
0.9L031452.6
0.91
4. 1084
22.27
0.998
0.002
3. 134
0.864
15. 8 3
C.94634226.2
0.95
4.3624
22.24
1.000
0.000
3.388
0.934
16.23
0.97036999.8
0.9 7
3.642
1.004
16. 53
0-98839773 .4
0.99
3.896
1.074
16.66
0.99642547.0
1.00
4.150
1.144
16.72
1.G0045320.6
1.00
4.404
1-214
16.73
1.0G048094.2
1.00
195
RUN 092974/1C0274
SFANWISE PROFILE TH=0
<3)
/
f
/
REX =
O.IOOOOE 01
REM =
6161.
RtH
/
3920. j
XVQ =
0.00 CM
0EL2 =
0^565
CM DEH2
0.
/
358 CM
UINF =
16.72 M/S DEI
L99 =
3.661
CM 0ELT99 =
3.
783 CM
Vise -
0.1530CE-04 P2/S DELI =
0.819
CM UINF
=
16.
73 M/S
PORT =
3
H
1.440
Vise
= 0.
15268E
-04M2/S
XLCC =
176.40 CM
CF/2 = 0.
lOOOOE 01
riNF
=
22
.30 DEG C
TPLATE =
36
.21 DEG C
YCCM)
Y/OEL
UIM/SI
U/UINF
Y +
U4-
YUMl TIDEG Cl
TBAR
TBAR
0,025
0.007
6.43
0.384
277.6
0.38
0. 0546
31.28
0.355
0.645
0.028
0.008
6.46
0.386
305 .4
0.39
0.0571
31.12
0.366
0.63 4
0.030
0.008
6.76
0.404
333.2
0.40
0.0597
30.66
0.398
0.602
0.033
0.009
6,97
0.417
360.9
0.42
0. 0o22
30.38
0.419
0.581
0.038
0.010
7.47
0.447
416 ,5
0.98
0. 0o48
30.11
0.439
0.561
0.046
0.012
7.87
0.471
49^.7
0.97
0.0/24
29.44
0.487
0.513
0. 056
C.015
8.28
0.493
613.8
0.50
0.0825
28.71
0.539
0.46 1
0.069
0.019
8.70
0-520
749,0
0.52
O. 0952
28.22
0.575
0.425
0.084
0.023
9.02
0.539
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0.54
0. 1105
27.66
0.615
0.385
0. 102
0,028
9.34
0.558
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0.80
0. 1308
27.24
0.645
0.355
0.122
0.033
9.53
C.570
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0. 1562
26.84
0.673
0,327
0. 147
0.040
9.75
0.583
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0.58
0. 1 86 7
26.58
0.692
0.308
0.178
0. 048
9.99
0. 597
1993 .9
0.60
0.^222
26-29
0.714
0.266
0-213
0.058
10.23
0.612
2332 . 1
0.61
0.2629
26.09
0.728
0.272
0.254
0.069
10.41
C.622
2778 -9
0 .02
0.3086
25.84
0.745
0.255
0. 300
0.081
10.57
0.632
32/0.1
0.63
0.3619
25.68
0.757
0.243
0.351
C.095
10.70
0.640
,:>83i . 9
0 .64
0.9254
25.51
0-769
0.231
0.406
0. 110
10.85
C.649
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0.65
0.‘t889
25.38
0.778
0.222
0.467
0.127
10.94
0.654
5 1 06 .5
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0.5524
25.28
0.786
0.214
0.538
0. 146
10.99
0.657
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0.6139
25.20
0. 791
0.209
0.620
0.168
11.08
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0. 795
0.205
0. 721
0.196
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0.66
0.8069
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0.804
0.196
0.848
0.230
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0.67
0.9334
24.89
0.814
0.186
0. 963
0.262
11.25
0 . 67 310522 ■ 4
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24,84
0.817
0.183
I. 102
0.300
11.4 1
0. 08212049.
0. 68
1.1874
24.76
0.823
0.177
1. 229
0.334
11.57
0.69213^37.5
0,69
1.3199
24.66
0.831
0.169
1.356
0.369
1 l.BO
0 ■ 706 1 4o25 > 7
0.7 1
1.9919
24.57
0.837
0.163
1.483
0.403
11.99,
0.71716213.9
0,72
1.8689
24,47
0.844
0.156
1.610
0.438
12.27
0.73417602.1
0.73
1.8224
24.22
0.862
0.138
1.737
0.472
12.54
0.75016993 .3
0.75
2.0764
23.99
0.879
0.12 i
1.864
0.507
12.84
0.76820378 .4
0. /7
2.3304
23.71
0.899
0.101
2. 118
0.576
13.47
0.80523154.8
0.81
2.8849
23,44
0.918
0.082
2. 372
0.645
14.16
0.84725931. 1
0.85
2.8385
23.17
0.938
0.062
2.626
0.714
14.80
0.8852870/. 5
0.88
3,0924
22.90
0.957
0.04 3
2. 880
0. 783
15.38
C.92031483.8
0.92
3.3964
22.68
0-972
0.028
3.134
0.852
15.87
C .94939260.2
0.95
3.6004
22.52
0.984
0.016
3. 388
0.921
16.27
0.97337036.5
0-97
3.8599
22.42
0,992
0.008
3.642
0.990
16.50
0.98739812 .9
0.99
9. 1089
22.35
0.996
0.004
3. 896
1.059
16.6 7
0.99742589,2
1.00
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22.32
0.999
0.001
4. 150
1.128
16.69
0 .99843365. 6
1.00
4,61 69
22.30
1.000
0.000
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1.197
16. 73
1.00098141 .9
1.00
196
mil
if
RUN 0S2974/100274 SFANWISE PROFILE TH=0 (41
REX
«
O.IOOOOE 01
REM =
5769.
REH
3991 .
xvd ^
SB
0.00
CP
DEL2 *
0.527
CM
0EH2
0.364 CM
UINF
ae
16.74
M/5
DBLy9=
3.656
CM
DELT99
3.760 CM
Vise
PORT
X
-M
0.15306E-04
4
P2/S
DELI =
H =
0.736
1.396
CM
UINF
Vise
_
16.75 M/S
0.15268E-04 M2/S
XLdC
X
176.40
CM
CF/2 = O.IOOOOE Oi
TiNF
TPLATE
X
22.30 DEG C
36.21 DEG C
Y(CM)
Y/DEL
U ( M/ S )
U/UINF
7 +
U +
YiCMJ
T(DEG C)
TBAR
TBAR
0.025
0.007
6.54
0.391
277.9
0.39
0.0546
31.08
0.369
0.631
0.028
0.008
6.85
0.409
305.6
0.41
0.0571
31.03
0.372
0.628
0.030
0.008
7.13
0.426
333.4
0.43
0.0597
30.76
0.392
0.608
0.036
0.010
7.55
0.451
389.0
0.45
0.0622
30-35
0.421
0.579
0.043
0.012
8.01
0.478
472.4
0.48
0.0673
29.73
0.466
0.534
0.053
0.015
8.40
0.502
583.5
0.50
0.0749
29.11
0.510
0.490
0.066
o.oie
8.81
C.526
722.4
0.53
0.0851
28.51
0.554
0.446
0.081
0.022
9.18
0.548
889 .2
0.55
0.0978
27.97
0.592
0.408
0.099
0.027
9.47
0.566
1083.7
0.57
0.1130
27.47
0.629
0.371
0.119
0.033
9.66
0.577
1305.9
0.58
0.1333
27.11
0.655
0.345
0.145
0.040
9.94
0.593
1583, 8
0.59
0.1587
26.78
0.678
0.322
0.175
0.048
10.13
0.605
1917.2
0.60
0.1892
26.50
0.698
0.302
0.2U
0.058
10.36
0.620
2306.3
0.62
0.2246
26.27
0.715
0.285
0.251
0. 069
10.61
0.634
2750.8
0.63
0.2654
26.02
0.732
0.268
0.297
0.081
10.83
0.647
3.^51 .0
0.65
0.3111
25-81
0. 748
0.252
0.348
0.095
11.01
C.6S8
3806. 7
0.66
0.3645
25.64
0.760
0.240
0.404
0.110
11.17
0.667
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0.67
0.4280
25.48
0-772
0.228
0.465
0.127
11-27
0.673
5084,9
0.6 7
0.4915
?5.38
0.779
0.221
0.536
0.147
11.42
0.662
5862 .9
0.68
0.5550
25.27
0.787
0.213
0.617
0.169
11.55
C.690
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0,69
0.6185
25.18
0.793
0.207
0.719
0.197
11.65
C.696
7863 .5
0.70
0.6820
25.12
0. 798
0.202
0.846
0.231
11.78
C.704
9252,8
0.70
0.8090
25.00
0. 806
0.194
0.960
0.263
11.89
0.71010503.2
0-71
0.9360
24.89
0.814
0.186
1.138
0.311
12.11
0.72312448.2
0.72
1.0630
24.77
0. 822
0.178
1.354
0.370
12.48
C. 74514810.0
0,75
1.1900
24.69
0.828
0.172
1.608
0.440
12.91
0.77117588,6
0.77
1.3170
24.59
0.836
0.164
1.862
0.509
13.4 1
C. 80120367.2
0.80
1.4<»40
24.47
0.844
0.156
2.116
0.579
13.97
0.83423145 .9
0.83
1.5710
24.34
0.854
0.146
2.370
Q.648
14.45
0.86325924.5
0.86
1.8250
24.15
0. 867
0.133
2.624
0.718
14.99
0-69526703.1
0.69
2.0790
23,90
0.885
0.115
2. E78
0.787
15-50
0.92631461. 7
0.93
2-3330
23-69
0.900
0.100
3. 132
0.857
15.95
0.95234260.3
0.95
2.5870
23.44
0.918
0.082
3.3€6
0.926
16.30
0.97337038.9
0.97
2.8410
23.15
0.939
0.061
3.640
0.996
16.53
0.98739817.5
0.99
3.0950
22.90
0.957
0.043
3.894
1.065
16.68
0.99642596.2
1.00
3.3490
22.73
0-969
0.031
4.148
1.135
16.75
1.C0045374.6
1.00
3.6030
22.53
0.983
0.017
3.857
22.42
0.992
0.00 8
4.111
22.32
0.999
0.001
4.365
22.30
1.000
0.000
197
RUN 092974/100274 SF^NWISC PROFiLt TH=0 (i»i
REX =
O.IOOOOE 01
REM =
6654.
REH
= '
3910.
XVO =
0-00 CM
0EL2 =
0.609
CM DEH2
S
0.
357 CM
UINF *
16.73 M/S DEL99=
3.805
CM DELT99 =
3.
909 CM,
Vise =
0.15309E-04 H2/S DELI =
0.907
CM UINF
=
16.
73 M/S
PORT *
5
H *
1.490
Vise
= 0.
152 66E
-04 M2/S
XLOC =
176.40 CM
CF/2 * 0.
lOOOOt 01
TINF
=
22
.29 DEG 1
TPLATE =
36
. 19 DEG 1
Y<CMI
Y/DEL
U(M/S)
U/LINF Y*
U +
Y(CM) T(OEG C)
TBAR
TBAR
0. C25
0.007
6 .99 .
0.418 277.5
0.42
0. 0546
28.73
0.537
0.463
0.028
0.007
7.22
G.431 j05.3
0.43
0.0371
28,21
0. 574
0.426
0.030
0.008
7.49
C.448 333.0
0.45
0. U597
27.86
0.599
0.401
0.036
0.009
7.83
G.468 388.5
0.4/
0 .0o48
27.39
0.633
0.367
0. 043
0.011
8.13
0.486 471.8
0.49
0.U724
27.03
0.659
0.34 1
0.053
0.014
8. 30
C.496 582.8
O. 3 U
0.0825
2 6.74
0.680
0.320
0.066
0.01 7
8.44
C.504 721.5
0.50
0.0952
26-51
0.696
0.304
0.C81
0.021
8.49
C.50 8 686.1
0.51
0.1105
26,35
0. 708
0.292
0. 102
0,027
8. 44
C. 50 5 11 10.1
0.5 0
0. 1308
26.18
0. 720
0.280
0. 122
0.032
8.47
0.506 1332.1
0.51
0. 1 56^
25.99
0.734
0.266
0. 147
0. 03 9
8.60
0. 514 1609.0
0.51
0.1943
25.64
0. 759
0.241
0. 178
0.047
8.68
0.519 1942.6
0.52
0.2451
25.09
0. 799
0.201
0.213
0.056
8.93
C.534 2331.1
0.53
0.2959
24.77
0.821
0.179
0.249
0.065
8.99
0.537 2719-7
0.54
0.3467
24.77
0.821
0.179
0.290
0.076
9.24
0.552 3163-7
0.53
0.-3975
24.87
0. 814
0.186
0.335
0.088
9,43
C.564 3603.2
0 • 30
0.4433
25.00
0.805
0.195
0.386
0.101
9.61
C.575 4218.3
0.57
0.4991
25.11
0. 797
0.203
0.442
0.116
9.81
0.586 4828.8
0.59
0. 5499
25.21
0. 790
0.210
0.503
0. 132
10. OC
0.598 5494.8
0.60
0.6007
25.29
0,784
0.216
0.579
0.152
10.27
0.614 6327.4
0.61
0.6315
25.34
0. 780
0.220
0.681
0.179
10.47
C.626 7437.5
0.63
0.7023
25.37
0.778
0.222
0.808
0.2 12
10.69
0.639 6623,0
0 ,o‘t
0.7331
25,37
0, 778
0,222
U. 960
0.252
10.92
C. 65310490, 2
0 .0 5
0.6039
25,37
0. 778
0.222
1. 138
0.299
11-18
C. 66812432. 6
0.6 7
0.6547
25.37
0.778
0.222
1.354
0.356
11.54
C. 69014791 .7
0.69
0.9055
25.32
0. 782
0.21 8
1.6C8
0.423
12.06
0.7221/566.6
0.72
0.9563
25.25
0,787
0.213
1.862
0.469
12.64
0. 75620342 .0
0.7o
1.0071
25.22
0. 789
0.21 1
2. 116
0. 556
13.25
0.79223117. 2
0,79
1.0579
25.17
0. 793
0.207
2.370
0.623
13.8 1
C. 62625892 ,4
0.83
1.1214
25.07
0.800
0.200
2.624
0.690
l‘t.40
G . 86 1 2 6o67 • 5
0.86
1.1649
25.01
0.804
0.196
2.878
0.756
14.99
0 .69631442 . 7
0.9O
1.3119
24.89
0.813
0.187
3. 132
0.823
15.53
C. 92834217 .9
0.93
1.4389 .
24.74
0.823
0.177
3.386
0.890
15.97
C. 95530993. 1
0.95
1.5659
24.61
0.833
0.167
3.640
0.957
16.36
0,97839768.2
0 .98
1.6199
24.37
0.850
0,150
3.894
1.023
16.58
C .9914^543 .4
0.99
2.0739
24.11
0. 869
0.131
4. 148
1.090
16. 64
0.99543316. 6
0.99
c.izn
23.86
0.887
0.113
4.402
1.157
16.71
C,9994uu93.a
1 .00
2.5819
23.60
0-905
0.095
4.656
1.224
16. 73
1. C0050866.9
1.00
2.8359
23.34
0-924
0.076
3.090
23.07
0.944
0.056
3.34>»
22.82
0. 962
0.03 8
3.598
22.62
0.976
0.024
3 . 632
22,45
0.988
0.012
4.106
22.34
0.996
0.004
4.36 0
22.29
1.000
0. 000
198
RUN 0^2974/100274
SPAKWISE PfiOPlLE TH=0
I6t
REX
M
O.IOOOOE 01
REH - 6814.
REH
3409.
XVO
.
0.00
CM
DEL2 = 0.t>2i*
CM
JEH2
—
0.312
CM
UINF
*
16.70
M/S
DEL94= 3.800
CM
0ELT99
-
3.999
CM
Vise
0. 15314F.-04
M2/S
DELI = 1.216
CM
UINF
=
16.70 1
M/S
PORT
*
6
H = 1.947
Vise
-
0.15266E-04
M2 /S
XLCC
ss
176.40
CM
CF/2 = li.lOOOOE 01
TINF
=
22.29
DEG C
rPL ATE
36.15
DEG C
YICM)
Y/DEL
U(M/S)
U/LINF
Y +
U +
Y(CM>
TIOEG C»
TBAR
TBAR
0.025
0.007
0.00
0.000
277.0
0.00
0.0546
32.18
0. 287
0.713
0.C84
0.022
O.OQ
C.OOO
914.3
O.UU
0.0673
31.27
0.352
0.648
0.147
0.03 8
0.00
C.OOO
1606.9
O.OU
U. 0800
30,9 1
0.378
0.622
0. 173
0.045
0.00
C.OOO
1883 .9
0.00
0,092/
30.70
0.393
0.607
0.198
0.051
0.00
0.000
2161.0
O.UU
0. 1034
30.54
0.405
0.595
0.211
0.055
0.00
0.000
2299,5
0.00
0.1181
30.44
0.412
0.588
0.224
0.058
1.70
0. 101
2438.0
0.10
0.1308
30.28
0.424
0.576
0.236
0.06 1
2.82
0. 169
2576 .6
0.17
0.1435
30.16
0.431
0.569
0.249
0.064
3-69
0.22 1
2715.1
0.22
0.1562
30.04
0.441
0.559
0.262
0.068
4.55
0.273
2853.6
0.27
0. 1689
29.79
0.459
0.541
0.274
0.071
5.20
0.311
2992.1
0.31
0.1943
29.2 7
0.496
0.504
0.267
0.074
5.91
0.354
3130.7
0,35
0.2197
28.72
0.536
0.464
0.300
0.078
6.48
C. 388
3269.2
0.39
0.1943
27.92
0^594
0.406
0.312
0.08 1
6.98
0,418
3407. 7
0.42
0.2705
27.01
0.659
0.34 1
0.325
0.084
7.45
C.446
33*t6 .2
0.45
0.2939
25.83
0. 744
0.256
0.338
0.087
7.35
C. ^70
368*t ■ 7
0.4 7
J.32L3
24.7 2
0. 825
0.175
0.356
0.093
8.3 0
C.497
3906 .4
0.50
0.3467
24.06
0. 872
0.128
0.389
O.lOl
8.7C
0.521
4^iO. 8
0.52
0.3975
23.71
0.897
0.103
0.429
0.111
9.02
0.540
468.1 . 1
0.54
0.4483
23.74
0.895
0.105
0.460
0.124
9. 2 1
C. 551
5236.2
0.55
0.4991
23.86
0.887
0.113
0.541
0.140
9.31
G.557
5901 .1
0 .50
0. 5499
24.09
C. 870
0.130
0.617
0.160
9.33
C. 558
6732i3
0.56
0. 6 007
24.33
0-852
0.148
0.693
0.179
9,33
C .558
75v*3.4
0.56
0.6515
24.64
0. 830
0.170
0.770
0. 199
9.33
C.559
8394 .6
0.56
O. 7023
24.92
0.810
0.190
0.846
0.219
9.40
0.56 3
9225. V
0.56
0. 7531
25.17
0.792
0.208
0.922
0. 238
9.4 8
C. 56810056. 9
0.5 7
0.8039
25.35
0. 779
0.22 1
1.024
0.265
9.62
0.576iilb:>. 1
0.5 8
0.6547
25.48
0.770
0.230
1.100
0.284
9.71
C.581 11996.2
0 .50
0.9055
25.56
0. 764
0.236
1. 176
0.304
9. 8 7
0.59112o2 7.‘»
0.59
0,9 563
25.59
0.762
0.238
1.278
0.330
10.02
0.60013935 .6
0.6O
1.0O71
25.59
0. 762
0.23 8
1.405
0.363
10.29
0.61615320. 8
0.62
1.0379
25.57
0.763
0.237
1.557
0.403
10.66
0. 63610983. 1
0.6 4
1 . 1087
25.51
0.768
0.232
1.709
0.442
11.08
0.6 631 8o43 a 4
0.66
1.1395
25.42
0. 774
0.226
1.913
0.495
11.61
0. 69520861 . 6
0.7O
1.233 7
25.31
0.782
0.21 8
2. 141
0.554
12.30
C . 7 3 7 23 3 5 5 a 2
0./4
1.3119
25.21
0.789
0.21 1
2.395
0.620
13.06
0.78226125.7
0.78
1.4389
25.03
0.802
0.198
2.649
0.685
13.80
C. 82 628896 .2
O.do
1 .5059
24.88
0.8L3
0.187
2.903
0.751
14.5 1
C. 86931666. 7
O.o7
1.6929
24.73
0.824
0.176
3.157
0.817
15.18
C. 90934437 .2
0.91
1,8199
24.61
0.832
0.168
3.411
0.882
15. 76
0.9443/207.6
0.94
2.0/39
24.33
0.853
0.147
3.665
0.948
16.2 1
C. 97139978, 1
0.97
2.3279
24.04
0.873
0.127
3.919
1.014
16.5 1
0.98842 740.6
0.99
2.5819
23.78
0.893
0,107
4.173
1.079
16 .67
0,99845519.1
1.00
2. 8359
23.49
0.913
0.087
4.427
1.145
16. 71
L. 00048289. 6
1.00
3.0899
23.19
0.935
0.06 5
3.344
22.94
0.953
0.04 7
3.598
22.67
0,972
0.028
5.852
22.52
0.983
0.017
4.106
22.37
0. 994
0.006
4. 3 60
22.29
1.000
0.000
199
RUN 0S2S74/100274 SPANWIS6 PROFILE TH*0 17)
REX
O.LOOOOE 01
REM » 7734.
REH
> 4001.
XVO
—
0.00
CP
DEL2 - 0.699
CM
0EH2
= 0.363 CM
UINF
=
16.77
H/S
DEL99S 3.9i>4
CM
DELT99
« 4.055 CM
VI SC
=
0. 15158E-0^
P2/S
DELI > 1.13o
CM
UINF
= 16.82 H/S
PORT
7
H - 1.625
Vise
= 0.15265E-04 M2 /S
XLGC
=
176.^0
CP
CF/2 s O.IOOOOE 01
TINF
= 22.27 DEG C
TPLATE
= 36.21 DEG C
Y(CH|
Y/DEL
U(M/S)
U/LINF V*
U +
Y(CM)
T(OEG C)
TBAR
TBAR
0.025
0.006
6.32
C.377 281.0
0.38
0.0546
29.41
0.487
0.513
0.028
0.007
6.32
0.377 309.1
0.38
0.0571
28.94
0.521
0.479
0.030
0.008
6.35
C.379 337.1
0.38
0.05 97
28.54
0.550
0.45 0
0. 036
0.009
6.78
0.405 393.3
0.40
0.0o48
27.93
0.594
0.406
0.043
0. Oil
7.26
0.433 477.6
0.43
0.0724
27.46
0.628
0.372
0. 053
0.013
7.53
C.449 590.0
0.45
0.0825
27.05
0.657
0.343
0.066
0.017
7.64
0.455 73U.5
0.46
0.0952
26.79
0.675
0.325
0.081
0.021
7.55
C.450 899.1
0.45
0.1105
26.58
0.691
0.309
0. 102
0.026
7.43
C.443 1123.8
0,4**
0. 1308
26.39
0.705
0.295
0.122
0.031
7.36
0.439 1348.6
0.44
0.1562
26-24
0-715
0.285
0. 147
0.03 7
7.38
0.440 1629.6
0.**4
0.1943
25.93
0.738
0.262
0.178
0.045.
7.56
0.451 1908.7
0.45
0.2451
25.43
0.773
0.227
0.213
0. 054
7.91
0.472 2360.0
0.47
0.2959
24.96
0. 007
0-193
0.249
0.063
8.30
C.495 2753 .4
0.50
0.3467
24.84
0. 815
0.185
0. 290
0.073
8.63
C.515 3202.9
0.51
0. 3973
24.91
0.811
0-189
0.335
0.085
8.9 1
0.531 3708.6
0.53
0.4483
24.99
0. 805
0.195
0.366
0.098
9.04
0.539 **270-6
0.54
0-‘*99i
25.12
0. 796
0.204
0.442
0.112
9.12
0.544 4888.7
0.54
0.5499
25.26
0.785
0.215
0.5 03
0.127
9.16
C.546 5563.0
0.55
0.6007
25-35
0-779
0.22 1
0. 579
0.146
9. 15
C.546 o405.8
0.55
0.6515
25.48
0.770
0.230
0. 681
0.172
9.22
C.550 7529.7
0.55
0.7023
25.57
0.763
0.237
0.806
0.204
9.36
0.559 8934-5
0.56
0.7531
25.64
0.758
0.242
0.960
0.243
9.53
C .56810620.2
0.57
0.8039
25.67
0. 756
0.244
1. 138
0.288
9.71
0.57912586.9
0.58
0. 0347
25.69
0.755
0.245
1.354
0.342
10.00
C,5961-*V75. 1
0.60
0.9055
25.65
0.757
0.243
1.608
C.4C7
10.59
0.63117784.6
0.63
0.9563
25.62
0.759
0.241
1.662
0.471
11.26
0.67220594. 2
0.6 /
1.0071
25.57
0.763
0.23 7
2. 116
0.535
12.0 1
0.71623403 -o
0.72
1.0579
25.52
0. 767
0.233
2.370
0. 599
12.83
C. 76520213 .4
0-77
1.1214
2 5-44
0-772
0.228
2.624
0.664
13.56
C. 80929023.0
0.8 1
1. 1849
25-36
0.778
0.222
2. 678
0.728
14.28
C. 85231832. 5
0.85
1.3119
25.19
0-790
0.210
3. 132
0.792
14.99
0,89434042. 1
0.89
1.4389
25.05
0.801
0.199
3.3 86
0.856
15.6 1
0.93137*t5i .7
0.93
1. 3659
24.90
0.811
0.189
3. 640
0.920
16.17
C. 96440261 .3
0.96
1.8199
24.63
0-831
0.169
3.894
0.985
16.50
0.98443070.9
0.98
2.0739
24.36
0.850
0.150
4. 148
1.049
16.67
C. 99445880. 4
0.99
2.3279
24-09
0.869
0.L3I
4.402
1.113
16.75
C. 99948690 .0
i .00
2. 5ol9
23.83
0. 888
0.112
4.656
1.177
16-77
1.C0051H99.O
1.00
2.8359
23-52
0-910
0-090
3.090
23.24
0.930
0.070
3.344
22-95
0.951
0.049
3.598
22.67
0.S71
0.02 9
3.852
22.52
0.982
0.01 8
4.106
22.38
0.992
0.00 8
4. 360
22.30
0- 998
0.002
4. 6 l4
22.27
1.000
0.000
200
RUN 092974/100274
SP/NWISE PROFILE
TH»0
<81
REX *
O.IOOOOE 01
REM *
7031.
REH
=
4296.
XVO *
0.00 O'
DEL2 *
0.640
CM 0EH2
-
0.391 CM
UINF =
16.74 M/S DEL99a
3.896
CM 0ELT99 »
3.989 CM
Vise =
0.15195E-04 M2/S DELI «
0.953
CM UINF
=
16.77 M/S
PORT =
8
H
=
1.486
Vise
* 0.
15266E-
04 H2/S
XLGC =
176.40 CM
CF/2 = O.IOOOOE 01
TINF
22.
28 OEG 1
TPLATE *
36.
21 DEG 1
Y(CM) .
Y/DEL
U(M/S)
U/UINF
Y +
U+
YCCMi TIDEG C)
TBAR
TBAR
0.025
0.007
5.9C
0.353
279.8
0.35
0.0546
31.49
0.339
0.661
0.028
0.007
5.94
0.355
307.7
0.35
0.0571
31.23
0.357
0.643
0.033
0.008
6.32
0.378
363. 7
0.36
0.0622
30.53
0.408
0.592
0. 041
0.010
6.94
0.415
447.6
0.41
0.0698
29.82
0.459
0.541
0.051
0.013
7.56
0.451
559.5
0.45
0.0800
29.20
0.503
0.497
0.063
0.016
7.94
C.474
699.4
0.47
0.0927
28.63
0.544
0.456
0. 079
0.020
8.34
0.498
867.3
0.50
0.1079
28.12
0.581
0.419
0.C97
0.025
8.6 0
0.514
1063 .1
0.51
0. 1263
27.67
0.614
0*3 86
0. 117
0.030
8.84
C.528
1287.0
0.53
0.1537
27.34
0.637
0.363
0.142
0.036
9.06
0.541
1566.7
0.54
0.1641
27.01
0.661
0.339
0. 173
0. 044
9-31
0.556
1902.5
0.56
0.2197
26.70
0.683
0.317
0.208
0.053
9.56
0.571
2294.1
0.57
0.2604
26.49
0.698
0.302
0.249
0.064
9.77
0.584
2741.8
0.56
0.3061
26.21
0.718
0.282
0. 295
0.076
9.98
0.596
3245.4
0.60
0.3594
26.04
0.730
0.270
0.345
0.089
10.13
0.605
380'* .9
0.61
0.4229
25.85
0. 744
0.256
0.401
0.103
10.26
C.614
4420.4
0.61
0.4664
25.70
0.755
0.245
0.462
0.119
10.3 6
C.619
5091 .9
0.62
0.5499
25.60
0.762
0.23 8
0. 533
0. 137
10.45
C.624
5875.2
0.62
0.6134
25.50
0.769
0.231
0.615
0.158
10.50
0.627
6770.5
0.63
0.6769
25.44
0.774
0.226
0. 716
0.184
10.58
0.632
7889.6
O.o3
0.6039
25.30
0.783
0.217
0.843
0.216
10.63
0.635
92 88.4
0.63
0.9309
25.21
0.790
0.210
0.958
0.246
10.74
0.64210547 .4
0.64
1.0579
25.09
0.799
0.201
1. 135
0.291
10.88
C. 65012505. 8
0.65
1.1649
24.99
0.806
0.194
1.351
0.347
11.20
0.66914883 .9
0.67
1.3119
24.89
0.813
0.L87
1.605
0.412
11.66
0.69717681 .6
0.70
1.4369
24.79
0.820
0.180
1.859
0.477
12.16
C. 72820479.3
0.73
1.5659
24.64
0.831
0.169
2.113
0.542
12.75
0.76223277.1
0.76
1.6199
24.43
0.846
0.154
2.367
0.607
13.36
0. 79 826074.8
0.60
2.0739
24.19
0.863
0.137
2.621
0.672
13.99
0. E3628872 .5
0.84
2.3279
23.96
0.880
0.120
2.675
0.738
14.66
0.87631670.2
0.68
2.5619
23.71
0.898
0.102
3. 129
0.803
15.23
0.91034467 .9
0.91
2.8359
23.44
0.917
0.083
3. 383
0.66 8
15,79
0.94337265.7
0.94
3.0699
23.19
0.935
0.065
3.637
0.933
16.24
0.97040063.4
0.97
3.3439
22.90
0.956
0.044
3.891
0.998
16.53
0.988^2861.1
0.99
3.5979
22.64
0.975
0.02 5
4. 145
1.063
16.71
0.99845658.8
1.00
3.6519
22-50
0.984
0.016
4.399
1.129
16.74
1.00048458.6
1.00
4.1059
22-37
0.994
0.006
4.360
22.30
0.999
0.001
4.614
22.29
1.000
0.000
201
RUN 0S297A/ 100274
SPANMiSt PROFILE TH=U (91
REX »
XVO »
UINF =
Vise ®
PORT »
XLOC =
Y(CM)
0.025
0.C2 8
0.033
0.041
0. 051
0.063
0. C79
0.097
0.117
0. 142
0. 173
0.208
0.249
0.295
0.345
0.401
0.462
0.533
0.615
0. 716
0.843
0. 958
1.097
1.224
1-351
1.478
1. 605
1.732
1. 859
2. 113
2. 367
2.621
2.675
3. 129
3-383
3-637
3. 891
4. 145
4.399
4.653
O.IOOOOE 01
REM =
6381.
REH
3=
4181.
0.00 CP
DEL2 =
0.584
CM 0EH2
0.
381 CH
16.78 M/S DEL99=
3.859
CM DELT99 =
3.
950 CM
0.15365E-04 H2/S DELI =
0.829
CM UINF
=
16.
76 M/S
9
H
1.419
Vise
II
o
•
L5263E
-04 M2/S
176.40 CM
CF/2 = 0.
lOOOoE 01
TINF
=
22
.25 DEG 1
7 PL ATE =
36
.25 DEG 1
Y/DEL
U(H/S)
U/LINF Y +
U +
Y(CM) TIDEG C)
TBAR
TBAR
0.007
6.51
C.388 277.5
0.39
0. 0546
31 .26
0.356
0.644
0.007
6.53
0.389 305.2
0.39
0.0571
31.15
0.364
0.63 6
0.009
7.0 1
G.417 360-7
0.4<i
0.059/
30.69
0.397
0.603
O.Oli
7.56
0.450 443 . 9
0,45
0*0622
30.30
0.425
0.575
0.013
8.1 1
0.483 554.9
0.48
0. 0648
30.08
0.441
0.559
0.016
a. 60
0,513 693 .7
0.51
0.0724
29,36
0.492
0.508
0.020
8,95
C.534 860.1
0.53
0. 0825
28.67
0.541
0.459
0.025
9.29
G.553 1054. 4
0.55
0.0952
28.09
0.583
0.417
0.030
9.58
0,571 i276.3
0.57
U. 1105
27.58
0.619
0.381
0. 03 7
9. 79
0.583 1553,6
0.:>8
0. 1308
27.11
0.653
0.34 7
0.045
10.01
C.597 1886.8
0.60
0.1362
26.76
0.678
0.322
0. 054
10.25
C.611 2275.2
0.61
0. i do 7
26.47
0.699
0.30 1
0.064
10.43
0.622 2719.2
0.62
0.2222
26.24
0. 715
0.285
0.076
10.62
C.633 3218.6
0.63
0.2O29
25.97
0.734
0.266
0.090
10.78
0.642 3773.5
0. 69
O .3086
25.83
0.745
0.255
0. 104
10.95
C.652 438^,0
O.o5
0.3619
25.63
0.759
0.241
0. 120
11.03
C.657 5049.9
0 .6o
0 • 4254
25.48
0.769
0.231
C. 138
11. 1 C
C . 66 1 5626 . b
0.66
0.4889
25.38
0.776
0.224
0. 159
11.2 1
0.668 b71t-7
0.67
0.5324
25.30
0.782
0.218
0.186
11.25
C.670 7824.5
U.o7
0.6159
25.20
0. 789
0.21 1
0.219
11.37
0.678 9211.9
0.68
0.6794
25.17
0. 792
0.208
0.248
11.52
C ■ 686 IOh-oO ■ 4
0.69
0 .80o4
25.04
0.801
0.199
0.284
11.67
0.69511986.5
0. 7o
0.9334
24.95
0.807
0.193
0.317
11.62
0.70413373 .8
0.70
1 • 0604
24.87
0.813
0.187
0.330
11.98
0.71414761 .2
O./l
l.ld74
24.79
0,819
0.181
0.383
12.22
C .728ibl48 .5
0.73
i.3144
24.71
0.825
0.175
0.416
12.44
0. 74117535.8
0.74
1.4414
24.59
0.833
0.167
0.449
12.6?
0.75518923 .1
0. 76
1.5084
24.49
0.840
0.160
0.482
12.96
0.77220310.5
0.7 7
1.8224
24.2 7
0.856
0.144
0.548
13.43
C. 80023085. 1
0.80
2.0764
24.04
0.872
0.128
0.613
13.98
C. 83325859. 8
0.83
2.3304
23.79
0.890
0.110
0.679
14.51
0.8652863^.4
0.86
2.5844
23.55
0.907
0.093
0.745
15,08
0.89831409 . 1
0.90
2.8385
23.30
0.925
0-075
0.811
15.57
0.93
3-0924
23.05
0.943
0.05 7
0.877
16.03
0 .955 jo958 .4
0.95
3 . 3464
22.79
0.962
0. 03 8
0.942
16.38
0.97639733.0
0.98
3.O004
22.58
0.976
0.02 4
1.008
16,62
C.990»2507.7
0.99
3.8544
22.43
0.987
0.013
1.074
16.74
C-997452 82. 3
1.00
4.1084
22,33
0.994
0.006
1.140
16.78
1.00048057,0
1 .00
4.3624
22.27
0.999
0.001
1.206
16. 79
1.C005J831. 7
1 .00
4.6164
22.25
1.000
-0.000
202
RUN 092974/100274
SPiANWlSt^ PROFILE rH=U (lOi
REX
9
O.IOOOOE 01
REH
< 6720.
REH
9
4158.
XVO
X
0.00
CP
0EL2
* 0.612
CN
DEH2
9
0.379 CM
UINF
=
16.72
M/S
DEL99
'« 3.831
CM
0fcLT99
9
3.934 CM
Vise
9
0.15224E-04
M2/S
DELI
> 0.908
CH
UINF
=
16.75 M/S
PORT
9
10
H
« 1.483
Vise
X
0.15265E-04 M2/S
XLOC
9
176.40
CM
CF/2
= O.IOOOOE 01
TiNF
9
22.27 OEG C
TPLATE
=
36.23 OEG C
Y«CMI
Y/DEL
U(H/S)
U/UINF
U+
YICMJ
TIOEG Cl
TBAR
TBAR
0.025
0.007
6.16
0.368
279.0
0.37
0.0546
31.38
0.347
0.653
0.028
0.007
6.3 1
0.377
306.9
0.38
0.0571
31.22
0.359
0.641
0.033
0.009
6.78
0.405
362.6
0.41
0.0597
30.78
0.391
0.609
0.041
0.011
7.32
0.438
446.3
0.44
0.0648
30.16
0.435
0.56 5
0.051
0.013
7.82
0.466
557.9
0.47
0.0724
29.51
0.482
0.518
0.063
0.017
8.23
0.492
697.4
0.49
0.0825
28.79
0. 533
0.467
0. C79
0.021
8.63
0.516
864.8
0.52
0.0952
28.20
0.575
0.42 5
0.097
0.025
9.01
0.539
1060. 1
0.54
0.1105
27.65
0.615
0.385
0.117
0.030
9.20
0.550
0.55
0.1308
27.16
0.650
0.35 0
0. 142
0.03 7
9.49
0.567
1562.2
0.57
0.1562
26.81
0.674
0.326
0. 173
0.045
9.69
0.580
1896.9
0.58
0.1867
26.45
0.700
0.300
0.208
0.054
9.90
0.592
2287.5
0.59
0.2222
26.22
0.717
0.283
0.249
0.065
10.02
0.599
2733 .8
0.60
0.2629
26.04
0.730
0.270
0.295
0.077
10.13
0.606
3236.0
0.61
0.3086
25.85
0.744
0.256
0.345
0.090
10.20
0.610
3793. 9
0.61
0.3619
25.73
0.752
0.248
0.401
0.105
10.23
0.612
4407.6
0.61
0.4254
25.62
0.760
0.240
0.462
0.121
10.23
0.612
5077,1
0.61
0.4889
25.54
0.766
0.234
0.533
0.139
10.25
0.613
5858.2
0,61
0.5524
25.47
0. 771
0.229
0.615
0.160
10.25
0.613
6750.9
0.6 1
0-6159
25.40
0.775
0.22 5
0.691
0.180
10.28
0.615
7587,8
0.61
0.6794
25.34
0.780
0.22 0
0.767
0.200
10.36
0.620
8424.6
0.62
0.3064
25.24
0.787
0.213
0.843
0.220
10.41
0.623
9261 .5
0.62
0.9334
25.13
0.795
0.205
0.919
0.240
10.49
0.62710098.4
0.63
1.0604
25.01
0.804
0.196
1.021
0.267
10.70
0.64011214.3
0.64
1.1874
24.91
0.811
0.169
1.097
0.286
10.81
0.64612051.1
0.65
1.3144
24.84
0.816
0.184
1.224
0.320
11.10
0.66413445 .9
0.66
1.4414
24.73
0.824
0.176
1.351
0.353
11.38
0.68114840.8
0.68
1.S684
24.61
0.832
0.16 8
1.478
0.386
11.62
0.69516235.6
0.70
1.8224
24.41
0.847
0.153
1.605
0.419
11.88
0.71017630.4
0.71
2.0764
24.16
0.865
0.13 5
1.732
0.452
12. 18
0.72819025.2
0. 73
2.3304
23.87
0. 885
0.115
1. 659
0.485
12.52
C. 74920420.0
0-75
2.5844
23.62
0.903
0-097
2. 113
0.552
13. 19
0.78923209.6
0.79
2.8385
23.34
0.923
0.077
2.367
0.618
13.83
0.82725999.2
0.83
3.0924
23.05
0.944
0.056
2.621
0.684
14.45
0. 86428788.8
0.86
3.3464
22.80
0.962
0.03 8
2.875
0.750
15.01
0.89831578.4
0.90
3.6004
22 .62
0.975
0.025
3. 129
0.817
15.35
C. 91834368.0
0.92
3.8544
22-45
0.987
0.013
3.383
0.883
16.00
0.95737157.7
0.96
4.1084
22.32
0.996
0.004
3.637
0.949
16.33
0.97739947 .3
0.98
4.3624
22.29
0.999
0.001
3.891
1.016
16.56
0.99042736.9
0.99
4.6164
22.27
1.000
0.000
3.891
1.016
16.56
0.99042736.9
0.99
4. 145
1.082
16. 7C
0.99945526.5
i.OO
4.399
1.148
16.72
1.00048316.1
1 .00
203
RUN 0S2974/100274
SPANWrSE PROFILE TH*0 ULi
REX =
O.IOOOOE 01
REM =
7255.
REH
=
4079.
XVO »
0.00 CM
DEL 2 =
0.659
CM DEH2
at
0.
372 CH
UINF *
16.72 M/S DEL99=
3.907
CM DELT99 =
3.949 CM
Vise =
0.15196E-04 H2/S DELI =
1.099
CH UINF
16.
76 M/S
PORT =
11
H
=
1.667
Vise
* 0.
15266E
>04 M2/S
XLOC =
176.40 CM
CF/2 = 0.
lOOOOE 01
TINF
22
.28 OEG C
TPLATE =
36
.19 DEG C
YICM)
Y/DEL
U(M/S>
U/OINF
Y +
U*
Y4CM) T(OEG C)
TBAR
TBAR
0* 025
0.007
4.94
C.296
279.4
0.30
0.0546
31.97
0.304
0.696
0.030
0.008
4.97
0.297
335.3
0.30
0.0571
31-81
0.315
0.685
0.033
0.008
5.14
0.308
363.3
0.31
0.0597
31.45
0.341
0.659
0.036
0.009
5-51
0.329
391.2
0.33
0.0648
30-86
0.383
0.617
0.043
0.01 1
5.95
0.356
475.1
0.36
0.0724
30.18
0.432
0.56 8
0.053
0.014
6.34
0.379
586.8
0.38
0.0825
29.58
0.475
0.525
0.066
0.017
6.75
0.404
726 .6
0.40
0.0952
28,99
0.518
0.482
0.061
0.021
7.11
C.425
894.2
0.43
0.1105
28.49
0.554
0.446
0.099
0.025
7.34
0.439
1089,8
0.44
0,1308
27-98
0.590
0.410
0.119
0.031
7.59
0.454
1313.4
0.45
0.1562
27.61
0.617
0.363
0. 145
0.037
7.85
0.470
1592.9
0.4 7
0.1867
27.23
0.644
0.356
0.175
0.045
8.07
0.483
1928.2
0.48
0.2222
26.95
0.664
0.336
0.211
0.054
8«22
0.492
2319.4
0.49
0.2629
26.67
0.684
0.316
0.251
0.064
8.34
0.499
2766.5
0.50
0.3086
26.48
0.699
0.301
0.297
0.076
8.45
C.506
3263.5
0.51
0.3619
26.31
0.710
0.290
0.348
0.089
8.44
0.505
3828 .4
0.51
0.4254
26.17
0.721
0.279
0.404
0.103
6.46
0.506
4443.2
0.51
0.4889
26-04
0.730
0.270
0.465
0.119
8.40
0.503
5113.9
0.50
0.5524
25,94
0.737
0.263
0.536
0.137
8.36
C- 500
5896.3
0.50
0.6159
25-81
0.747
0.253
0.617
0.158
8.33
0.498
6790.6
0.50
0.6794
25.73
0.752
0.248
0.693
0.177
8.32
0.49 8
7628. 9
0.50
0.8064
25.56
0. 764
0.236
0.770
0.197
8.42
0. 504
8467.3
0.50
0.9334
25.41
0,775
0.225
0. 846
0.216
6.56
C.512
9305.6
0.31
1.0604
25.26
0.766
0.214
0.922
0.236
8.77
0.52 510144.0
0.52
1,1874
25.15
0.794
0.206
1.024
0.262
9.11
0.54511261 .7
0.55
1.3144
25.00
0.805
0.195
1.125
0.288
9.56
0.57212379.5
0.3 7
1.4414
24.90
0.612
0.188
1.227
0.314
9,92
0.59313497.3
0.59
1.5684
24.81
0.818
0.182
1. 354
C. 346
10.3 1
0.61714894.0
0.62
1.8224
24.58
0.835
0.165
1.461
0.379
10,69
0.63916291,8
0.64
2.0764
24.31
0.854
0.146
1.608
0.41 1
11,03
Q.65917OB9.0
0 >d6
2.3304
24.02
0.875
0.12 5
1.735
0.444
11.39
0.68119036.3
0.68
2.5844
23.71
0.698
0.102
1.662
0.477
12.04
0.72020483.5
0.72
2.8385
23.40
0.919
0.081
2. 116
0.542
12.56
C. 75123278.0
0.75
3.0924
23.12
0.940
0.060
2.370
0.607
13.34
0.79 8260 72. 5
0.80
3,3464
22-85
0.959
0.041
2.624
0.672
14.11
0. 84428867.0
0.84
3.6004
22.64
0.975
0.025
2.878
0.737
14.78
C e 88431661 .4
0.88
3.8544
22.47
0.9B7
0.013
3. 132
0.802
15.40
0.92134455. 9
0.92
4.1084
22.37
0.994
0.006
3.386
0.867
15.87
0.94937250.4
0.95
4.3624
22.30
0.S99
0.001
3.640
0-932
16.26
0.97340044.9
0.97
4.6164
22.29
I. 000
0.000
3.894
0.997
16.51
0.98742839.4
0.99
4. 148
1.062
16.65
0.99645633.8
1.00
4.402
1.127
16.72
1.00048428.3
1.00
204
SPAKWISE AVERAGE UF II L STATIONS
YICP)
U(rt/SJ
0/UlNF
T ICi
TBAP.
TBAR
0.055
6-77
0.^04
31.21
0.359
0.641
0.057
6.
0. 408
30.99
0.374
0.626
0.060
6.89
0-412
30. 65
0. 399
0.601
0.065
7.01
0.419
30.07
0.441
0.559
0.072
7. 16
0.428
29.49
0.482
0.518
0.083
7.33
0.438
2o.92
0.523
0.477
0.055
7.48
0.44/
28.45
0. 557
0.443
O.ilO
7,61
0.455
28.01
0. 589
0.411
o.iai
7,77
0.464
2 7.63
0.616
0.384
0.156
7.94
0. 4 75
.27.31
0.639
0.361
0.187
8.1^
0.485
26.95
0.66 5
0.335
0. 2 22
8.50
0.5 08
^8.47
0.699
0.301
0.263
9.07
0 • 542
26. 19
b. 719
0.281
0.3C9
9.d1
0. 5oo
25-75
0.751
0.249
0-362
9.82
0. 587
25. 46
0.772
0.228
0.^25
9.99
0.597
25.33
0.781
0.219
0.409
10,07
0.602
25.28
0-785
0.215
0.552
10.12
0. 605
25.2 6
0.786
0.214
0-616
10,15
0.60 7
25.26
0.786
0.214
0.679
10.18
0.609
25.27
0. 785
0-215
0.8C6
10.28
0.615
25. 2b
0. 786
0-214
1,060
10.63
0.636
25. ii
0, 797
0.203
1.167
1 0. uo
0.649
24.99
0.806
0. 194
1.314
11,10
0,663
24.88
0. 814
0.186
1.441
11.35
0.679
24. 75
0. 822
0. 178
1.568
11.62
0.695
24.63
0. 832
0.168
1.822
12.24
0. 732
24. 40
0. 848
0.152
2.076
12.90
0.771
24. 13
0. 867
0- 133
2.330
13.57
0.811
23- 87
0.886
0.114
2.584
14i23
0.351
23.60
0. 905
0.095
2.838
14.86
0. 888
23.32
0.925
0,075
3.052
15,41
0.922
23.05
0.945
0.055
3-346
15.92
0.96C
22.80
0.963
0. 03 7
3.6C0
16.30
0.9 75
22.36
0.978
0.022
3.854
16,55
0.989
22.44
0. 989
0.011
4.1C8
16.68
0.9^7
22. 33
0.996
0.004
4-362
16. 73
1.000
22.28
1. ooo
0.000
AVG UINF
= 16.73 M/
S AXG
Vise = 0.152 73c '04
M/6
AVG REM
= 6781.
AVG
REH - 3973.
A VG
H= 1-54
AVG TG =
36.21 DEG
C
205
oor>r>oOOo
Appendix III
STANTON NUMBER DATA REDUCTION PROGRAM
1
2
•a
A
R
6
7
8
10
1 1
12
13
It
STANTON NUMBER DATA R6 DUCT I ON PROGRAM
DISCRETE HOLE RIG NAS-2-l^336
THIS PROGRAM USES THE LINEAR SUPERPOS IT I CN PRINCIPLE TO
CALCULATE STANTON NUMBERS ANC OTHER INTEGRAL PARAMETERS AT THETA=
0- AND 1.
REVISED SEPTEMBER 1«75
REAL K
COMMON/ BLKl /PAMB, PSTAT»TREtOV,RHUM,PDYN
CCMMCN/ BLK2 /UI NP , TIf4 F ,TAD I AB t RHOG , VI SC , P R t CP
COMMON/ BLK3 /SA FR ( 12 ) ♦ C H 12 )t SMI 12 ) , F ( 1 2 ) t KM, AH » THE AT
COMMON/ BLK4 /TO( 43 ).T16(12),T2H2) ,TCAST( 12) ,TCAV(12),THa2)
CCMMCN/ BLK5 /Q1 12 ) ,HM (45 ) , V ( 1 2 ) , ODOT ( 36 )
COMMCN/ ELK6 /DXVG , CEND2 , CF , CREENI 36 ) ,DST( 36 ) , D COCT ( 36 ) , DTHI12)
DI MENSICN NRNI4) ,KOMMNT< 40 ) , TGI 12 ) , TE XI T ( 1 2) ,ST { 26 ) ,QFL0W(12) ,
1 X( 36) .REXI36) , REEM36) ,STN£B(36) ,STO( 36 ) , STCCL ( 36 ) , STHOT ( 36 ) ,
2 STSI 36),STSF(36) ,STCR(36), STHRI36) tSTSPI 36),SMC( 12),F0(12) ,
3 BHC0LI12) ,EH0T(12),REXC(36 1,RENC0L(36) , R ENFOT ( 26 ) ,THOI 12 ) ,
4 FBU2) ,D2H0T(36) , CTHGI 12) ,CSTO( 36) , ETA I 3 6 ) ,FH 1 12 ) , SF( 12 ) ,SFC( 12)
DI MENSICN NR NCI 4 ) ,S7HRBI 12 ) , KOMNTO I 40 )
DATA X/50. 3,52.3,54.3,56.3,56. 3,60. 3,62. 3,64.3,66.3,68.3,
1 70.3 ,72.3, 73. £2, 74. 8 5, 75. 88, 76. SI 5,7 7. S5, 78. 98, 80. 01, 8 1.04,
2 82.07,83.1, 84. 13, 85. 165,86.2,87.23,68.26,89.29,90.32,91.35,
3 92. 38, 9 3. 4 15 ,? 4. 45, 9 5.48,96. 5 1,97. 54/
C
C *1* READ PUN NUMBER /NO CONTROL PARAMETERS
C
C NRN
C I OUT
C
C
C KT
C
C
C KM
C
C
C L
C
c
c
c
c
c
c
C note: data SETS MUST EE STACKED FLAT PLAT E, M (T H= 0 ), M (TH= 1 ) ,
C M(TH=0) ,M (TH= 1) , ...
C
WRITE (6,900)
C*** + t + ^^**^**+>^*
C IPRINT = 0 TO PRl. NT . SUMMARY DATA SET ONLY
C IPRINT=1 TO PRINT ENTIRE DATA REDUCTION
c •
IPRINT=1
Q^,^Lm***^>t* ****-1i**-*
5 READ (5,10) (NRN( I) ,1 = 1,4) ,IOUT,KT ,KM,L
10 FORMAT (4A2, 12, 1 2, 12,1 2)
IF tlOUT.NE.O) GO TC 2000 .
8 DIG I T RUN NUMBER
PARAMETER TO TERMINATE PROGRAM
IOUT=0 TC READ DATA SET
I CUT NE 0 TO TERMINATE PROGRAM
DiATA TYPE F CR LINEAR SUPERPOS IT IC N
KT=0 FLAT PLATE GR HITH = 0)
KT=1 M(TH=1)
P ITCH/D I AME TE R RATIO OF HOLE ARRAY
KM=0 P/0 FIVE
KM=1 P/D TEN
TYPE OF FLAT PLATE STANTON NUMBER FCR ST NO RATIO
KEQ'JLRED TO SPECIFY L FOR TH= 1 RUN ONLY
L=0 STANTON NUMBER BASED ON ST-PE> HEATED STARTING
LENGTH CORRELATION
L=1 STANTON NUMBER BASED CN ST-REX UNHEATED STARTING
LENGTH CORRELATION
L=2 FUT PLATE STANTON NUMBER TEST DATA
206
c
C *2* READ EATA RU^ DESCR IPT I CN> A FORMAT COL 1-80
C
16 READ <St2) (KJMMNT(I)t I=l«40)
n 2 FORMAT (A0A2)
C
C * 2 * READ TEST CONDITIONS
C
C TAMB AMBIENT 7EMPERATURE IDEG F)
C PAMB AMBIENT PRESSURE 4INCHFS HG CORRECTED TC 32 DEG FI
C RHUM RELATIVE HUMIDITY (PERCENT)
C ThEAT SECONDARA AIR TEMR, HEATER BOX ( I-C TC t MV)
C CUD SECONCARY AIR FLOVMETER CURRENT SIGNAL (MVI
C
LC READ (5*20) TAMB »PAR3 » BHLPt THE ATfCI ( 1)
IS 20 FORMAT C7F10.0)
20 DO 22 1=2,12
21 22 Cl (I) = CI(1)
C
C READ TUNNEL DCNDITIQNS .
C
C TRECOV TUNNEL AIR RECCVEPY TEMPERATURE (I-C TC, MV)
C POYN TUNNEL AIR VELOCITY DYNAMIC PRESSURE ( INCHES H20)
C PST AT TUNNEL GAGE STATIC PRESSURE (INCHES H20 )
C XVO VIRTUAL CRIGIN, TBL, FfOM PGM PROFILE (INCHES)
C EN02 ENTHALPY THICKNESS, FRCM PGM PROFILE (INCHES)
C OXVO UNCERTAINTY IN XVC, FROM PGM PROFILE (INCHES)
C DEND2 UNCERTAINTY IN END2, FROM PGM PROFILE (INCHES)
C
22 READ (5,20) T REC OV , POYN, P STAT, X VO ,END 2,D XVC ,CE ND2
C
C *5* READ TEST SECTION CONOITIGNS
C
C TG(I) SECONCAPY AIR TEMPERATURE IN CAVITY (I-C TC , MV)
C TO(I) PLATE TEMPERATURE (I-C TC , MV)
C Q(I) PLATE PG<«ER (HATTS)
C VAR(I ) VARIAC SETTING
C SAFR(I) SECONDARY AIR FLOWMETER SIGNAL (MV)
C
>3 READ (5,25) ( TG ( I ) , TO ( I ) ,0 ( 1 1 , VAR ( I ) , SAF R( I ) , 1 = 1,12)
24 25 FORMAT (5F10.0)
C IF (SAFR(2),NE.0.I L=2
C
C * 6 * READ RECOVERY StCTICN CCNCITIONS
C
C TO(I) PLATE TEMPERATURE (I-C TC, MV)
C HM(I) HEAT FLU> METER SIGNAL (MV)
C
25 READ (5,26) ( T0( I ) ,H M ( I ) , I =1 9,45 )
26 26 FORMAT(2F10.0)
C
C * 7 * READ TEMPERATURES
C
C TCAST(I)TEST SECTICN CAVITY TEMPERATURE (I-C TC, MV)
C T16(I) SECONDARY AIR TEMPERATURE OUTSIDE CAVITY (I-C TC , MVI
C TEX IT( I ISECONDAPY AIR TEMPERATURE AT EXIT OF HOLE (I-C TC, MV)
C
27 READ (5,27) ( TCAST C I ) ,T 1 6( I ) ,TEXIT ( I ) , 1 = 1,12)
L
20
2?
3G
31
32
33
3^
2 5
3 6
3 7
3 £
4C
41
42
43
44
45
46
47
4 £
49
5C
51
52
5 3
54
5 5
56
57
56
59
ec
61
62
6 3
64
65
66
67
6 £
27 FCBMAT OFIO.OJ
C
C WRITE OUT ALL RAW DATA
C
IF<IPRINT.NE.OJ WRITS (6,9001
WRITE (6,40) (NRNd), 1 = 1,4)
40 FORMAT (10X,»R(Xn^ MA2,* DISCRETE HOLE RIG NAS-3- 14336*
1 , lOX, *STANTON NUMBER DATA*/)
WRITE 16,610) (KCMMAT(I), 1=1,40)
6 10 FORMAT (40X,40A2/)
IF (IPRINT.EO.O) GO TO 7772
WRITE (6,45)
45 FORMAT (lOX, 'UNITS: PANB(06G F),PAMB(1N HG) , RHUM ( PC T ) * /1 7X ,
1 *PSTAT(IN H20), TR£COV(MV), POYNdN H20 ) , KVQ(IN), TPLAT E ( MV I * /17
2X, *TGAS(MV) , OOOT(WflTTS), S A FR ( MV) ,HM ( MV I , CI(MV), THEAT(mV)*/)
WRITE (6,50) TAM3, F AM3,RhLM, THEAT
50 format (UX, 'TAMB = ‘ F6. 1, 5X,» FAMB=*F6.2,5X, *RELHUM = *F5.1,6X,
1 *TH3AT£R=*F6.2/)
WRITE (6,60) PSTAT,TRECCV, FD>N,XVC
60 FORMAT (iOX, • PST AT = ' F6 .2 , 5X , *TR ECCV= * F6- 3, 5X , ' P CYN = * F6 . 3 , 5X ,
1 • XVr=* F6.2//)
WRITE (6,7 0
70 FORMAT 110X,*PLATF* ,6X, •TFLAT6«,6X, 'TGAS* ,6X , *00 CT * , 4 X, *VARI AC»,
1 5X, 'SAFLOW* ,5X, *C LRR ENT * ,6 X ,* TCAST * , 5X, • T16 * , 5 X, • 7EXI T* / )
NPl = i
WRITE (6,75) NPl ,70 (1) ,0 (1 ) , VAR( 1 ) fTCASTU J
75 FORMAT ( iOX,. 13 , 7X, F 7 . 3 , 1 3X , F 7. 2 , 3X, F 7, 1 , 27X,F7.3)
WRITS (6,80) (I , T0( I ) ,TG (I ) , C(I ) ,VAR(II ,SAFB (I ) , C I (I) ,TCAST ( I ) ,
I Tlo( I I, TEX IT( I ), 1=2, 12)
80 FORMAT (1JX,I3,7X,F7.3,3X,F713,3X,F7.2,3X,F7.1,3X,F8.3,3X,F8.3,
1 5X, F7.3,F5.3,F9.3 )
WRI TE(6 , 71 )
71 FORMAT { /,! OX, »PL ATE *,6X, ‘TPLATE * ,6X, *HM* )
WRITt(6,72)( I,TO(I ),HM (I ), 1 = 13,45)
72 FORMAT (13X,I.3,7X ,F7.3,3X,F7.3)
7772 COXTINUE
C
C data CONVERSION BLOCK
C
C CCNVFpT all TFMPER.ATUP.es FRCM MV TO deg f
TREC CV = TC (TRFCOV)
TH£AT=TC(TFEAT)
DO So 1 = 1, 12
T0( I )=TC (TC( n )
tg (I )=tc(tg( in
tcast( I )=tc( tcas: ( n )
T16( I )=TC( T16(I ) )
T£XIT(I)=TC( TEXIT(I) )
SC CONTINUE
DO 91 1=13,45
91 TOd ) =TC(TC( I) )
C PLATE AREAS
A=18.^1.Sb£750/144.
C HOLE AREA,
A H={ 3. 1415 931*0.4 05 *0.406*0 .2 5)/ 144,
C COMPUTE WIND TUNNEL FLOW CONDITIONS
CALL TUNNEl
C COMPUTE secondary AIR FLGW RATE
CALL FLOW (KiERRORJ
IF (KERPGR.GT.O) RETURN
208
69
70
71
72
73
7A
75
76
77
78
79
80
81
82
83
8 ^
85
8 £
87
8E
89
9C
91
92
93
94
95
96
97
9 e
99
IOC
101
102
IC3
10 4
105
10 £
C CCMPUTE SECONDAR.V AIR FLQIt TEMPERATURES AKO QFLOh LOSS
CALL T2EFF (CFLOW)
C COMPUTE NET ENERGY TRANSFER FROM TEST SECTION AND RECOVERY
C REGION
CALL POWER I TINF »QFLOW»A)
C
C WRITE ALL CONVERTED DATA
IF ( IPR INT.EQ.O) GC TO 1108
C
WRITE (6t610) (KOHMNTI I) t 1-1,40)
WRITE (6,100)
ICO FORMAT (//,10X, ‘UNITS: TP LATEI OEGF I , 7GAS(CEG F), QDCT (WATTS ),• ,
1 /17X,«SAFL0W(CFMI,CFLLX (e7L/HR/SQFT),TEFF2C0EG F)»/)
WRITE (6,102)
102 FORMAT (lOX, ‘PLATE » ,6X, 'TPLATE • , 5X, * TEFF2 • , 5X , »T16 »,6X,‘Q0CT»j
1 6X ,*QFLUX» ,6X, • SAFLO Vi* , 6X , !TCAST* , 6X, • TGAS • , 6 X, • TE XI T * ,
2 6X,»TCAV*/)
WRITE (6,105) NP1,TQ(1),0( 1 ),QDCT(1 ),7CAST( 1),TCAV( 1)
105 FORMAT! lOX, 13, 7X,F 7-1 ,23 X,F7A2, 5X ,F7* 2 , 14X , F7. 1 ,20X,F10.1 )
WRITE (6,110) (I,T0(I),T2(I),T16(I),Q(I) ,QCOT( n,SAFR(I),
1 TCAST! I ),T-G(I ), TEXIT( I) ,TCAW( II, 1-2,12)
no FORMAT! 10X,I3,7X,F7.1,3X,F7-1,3X,F7. 1,3X,F7.2,5X,F7.2, 1X,F8.2,
1 5X,F7,1,3F10.1 )
WRITE (6,1061
106 FORMAT (/ ,10X, » PLATE ',6X, »TPL AT E* ,6X , * FM» , 5 X, ‘OFLUX*/)
WRITE (6, 1071 ( I,TO( I) ,HM(I ) , COOT ( I ) , I -13 • 3 6 )
107 FORMAT ( lOX, I3,7X, F7-3 ,3X,F7 *3, 3X,F7,2)
I -10 a
WRITE (6,108) I,T0(45)
1£8 FORMAT ( lOX, 13 ,7X, F7.3 )
C
C COMPUTE STANTON NUMBER
C
11C8 CONTINUE
XVI-X! D-XVO-l.O
IPD-5
IF (KM.EQ.l) IPD-10
C X REYNOLDS NUMBER BASED ON VIRTUAL ORIGIN TBL
201 FACT=UINF/(V ISC412 . )
DREX-F ACT* CXVO
DO 210 1=1,36
210 REX( I> =FACT* ( X( I )->V0)
C CCMPUTE STANTON NUMBERS
OF NON=RH CG*UI NF*CP*360 0.
DO 220 1=1,36
ST (I ) = CDCT (£ )/(DENCN*(TC(I )-TADIAB) )
C CST(I): UNCERTAI.NTV IN ST(I)
C DP : UNCERTAINTY IN MANCMETER PRESSURE , IN H20
OP-C.OC8
C CT: UNCERTAINTY IN TEMPERATURE, F
0T=0, 25
0ST( 1 ) = ST( I)*SORT(OCDOT( I )>*DCOOT( I )/(CDOT( I)*QDCT(I)) + DP>f‘DP/(4.*
1P0YN*PDYN)+0T’*DT/ ((T0( I ) -T INF)’* (T0( I )-T INF I ) )
220 CONTINUE
C CCMPUTE DEL2 ANC RECEL2 BASED ON ACTUAL ST-CA7A
CALL ENTFAL ( FAC T, ST, REE A ,ENC2)
C
IF ( IPRINT.EQ.O) GO TO 3310
WRITE (6,900)
WRITE (6,40) (NRN(I), 1=1,4)
209
107
108
109
lie
111
112
113
114
115
116
in
lie
119
12C
121
122
122
12A
125
126
127
126
129
130
131
132
132
134
135
136
137
138
139
14 C
141
142
142
144
145
146
147
148
149
150
151
152
153
154
TACBC=5.*(TAOIA3-3i •1/9.
TINFC = 5.*(TTNF-32. 1/9.
UINFMS»UINF«0.3048
XV0CM=XV0*2i54
RHCKM3=RH0G*16.02
VlSCI=VISC*fl*092 9
CPJKGK = CP*4184.
WRITE <6,3001 TADBC,UINFHS,TINFC,RH0KP3,VISCI, >V0CM,CPJKGK,PR
3CC FQPMAT<10X,*TADa=' F6.2 ,* DEGC UINF=» F12- 2, • P/S TINF=*F6.2
1* OEG eVlOX, •RH0=*F7. 3, * KG/M3 VI SC= • E 12.5 , ' «2/S XVC-*F7.1
2 • CM*/10X,«CP=» F8 .0, * J/KGK PR=»F14.3/>
WRITE (6,600) (KaMP^T(^, I>1,40)
600 FORMAT <10X,4aA2/i
3210 CONTINUE
C IF 2ND PLATE HAS NO SECCNDARX INJECTION , THIS PRCGRAM ASSUMES THAT
C IT IS A NO-BLOWING CASE.
IF (SM(2 ).EC.O.) GO TO 400
IF ( IPPINT.EG.O) GC TO 345
WRITE (6,310)
310 FORMAT! lOX * PLATE • , 3 X • X • , 5 X * REX ' , 9X * TO * ,6 X« R EENTH 7X • STANTON NO • ,
1 6X*DST»,6X*DREEN* , 4X* P* ,4X* t* ,6X» T2 • ,2X *THETA * ,3X • CTH* )
XCM=X( 1 )*2 -54
TEMPC = 5.»-( TC( I )-32. )/9.
WRITE (6,3201 NP 1 , XCM , REX < 1 * ,TEMPC , REEN ( 1) , ST ( 1 ) , DST ( 1 ) , DREEN ( U
320 FORMAT! 1 OX 1 3 , 2XF 5 . 1 , IX El 2. 5 , IXF6 . 2, 2 ( 2XE 12 . 5 ) , 2 XE9 .3 , 2 XF5 .0 )
DO 340 1 - 2,12
XCM=X( I )T2.54
T6MPC=5.’«(TOm-32. )/9.
TEMP2 = 5.*(T2( I)-32 . )/9.
WRITE <o,330) I ,XCP,R£X(I ),TEMPC,REEN(I J ,ST(I) ,DST( I),OREEN(I),
1SM(I ), F (I) ,TEMP2 ,TM I) ,DTH( I J
330 FORMAT! 10XI3,2XF 5. 1 , 1 XEl 2. 5 ♦ 1XF6 . 2 , 2 ( 2XE 12 . 5 ) , 2 XE9 .3 , 2XF5 .0 ,2XF5.2
1,F7.4, F6-2,F6-3, 2XF5.3 )
34C CONTINUE
DO 341 1=13, 36
XCM=X( I )*2.54
TEPPC=5.*(TOm-3 2. )/9.
WRITE (6,331) I, XCP ,REX (I ) ,TEMPC,REEN( I) ,ST( I),DST( I ),OREEN (I)
3 31 FORMAT ( 10X13, 2XF 5. 1 , 1 XEl 2 . 5 , 1XF6. 2 , 2 ( 2XE 12 . 5 ) , 2 XE9 .3 ,2XF5.0)
341 CONTINUE
WRITE (6.334) DRcX.CF
334 FORMAT ( /12X , • UN C ERTAI NTY IN RE X= • , F6.0 , 9X ‘UNCERTA INTY IN F = »,F7.5
1,* IN PATIO* )
GO TO 345
C
C STORE FLATPLATE EXPERIMENTAL DATA FOR STANTCN NUMBER PATIO
C
4CC DO 401 1=1,36
STNOB( I )=ST< I )
4 01 CONTINUE
WRITE (6,410)
410 FORM AT( 10X«PLATE ' ,3>* X«,5X» REX »,9X »T0 » ,6X • R EENTH’ , 7X* STANTON M3 • ,
1 6X»DST* ,6X» DREEN* ,5X ,»ST(THEQ) *,6X, 'PATIO*)
OG 420 1=1,36
STT=.0 29 5*PR**(-.4 )*(REX( I ))*»♦(-. 2)
IF (L.EC.l )STT=STT*(l.-( XVI/!X( I )- XVO) ) *♦. 9 ) >Mt (- 1. /9 . I
RATIC=ST(I )/STT
XCM=X(I )4*2.54
T£MPC=5.=MT0(I )-32.)/9.
WRITE (6,430) I ,XCP,REX(I),TEMPC,REEN(n,ST!I),OST(I),DREEN(I),
210
155
156
157
156
155
16Q
161
162
163
16 ^
165
16C
167
16£
165
170
I 71
17 2
173
llA
175
176
17 7
178
179
180
lai
182
183
18 ^«
185
186
18 7
168
189
190
191
192
19 2
194
19 *
196
197
198
199
200
201
20 2
2 03
204
20 5
1 STT»RATIC
430 FQRi^AT ( lOX I 3 , 2XF 5 . 1 f I XEl 2 . 5 , 1 XF6. 2 , 2 ( 2X E 12. 5 ) , 2XE9 .3 ,2 XF5 . 0,
1 E15.5fF9.3)
420 CONTINUE
IF (IPRINT.EQ.Ol WRITE 16,900)
GO TO 5
C
C
C STORE VALUES FOR TH=0
345 IF (KT.EQ.l) GO TO 260
C
350 DO 351 I =1 ,12
SMCI I ) = SMn )
FOI I )=F1 I)
THO(I)=TH(II
OTHOd )=DTHU)
STOl I)=ST( I J
OSTOn J=DST( I )
REXO( I )=REXI I )
351 CONTINUE
DO 352 1=13,36
STO( n=ST( I )
OSTO(I)=DST( I)
REXOI I ) = RE xm
352 CONTINUE
F ACTO=FACT
DFC=DF
00 353 1=1,4
3 53 NRNOII ) = NRNU )
00 354 1=1,40
354 KGMNTO (I) = l<0MMNT (I )
GC TC 5
C
C COMPUTE STANTON NUMBER AT TH=0 AND TH = 1 BY LINEAR SUPERPCSIT I ON
C
360 FAVO=0.
FA V=0-
THAV0=0-
THAV=0.
DO 361 1=2,12
THAVO=ThAVO+THO( I)
THA V=THAV+TH( I )
FAVO =FA VO*FCl I )
FAV= FAV + F< I >
361 CONTlNLE
THAVO=(ThQ(ll )+THOl 12) )/2.
THAV={TH(ll) +TH( 12 ) )/2 .
FAVO=FAVO/ll.
FAV=FAV/ 11.
FBAV=. 5*(FAV0«-FAV)
STCR( I ) = ST0I1 )/STNOE{ 1 )
STHR ( I } =ST C 1 ) /ST NOB II )
STHRBIl )=STHR ( II
THIl )=TH(2)
THOI 1)=TH0(2 I
DO 362 1=2,12
DENOM=ITHI I-l ) + TH II J ) /2--(THe( I-D+THCd )) /2 .
STSdl = (STO( ll-STI I n/DENOM
ONUH = (THO( I-ll+T HOI n 1/2.
STCCLI I )=STO (I H- DNUM^STS I I )
211
20 6
2C7
2C£
209
210
211
212
213
21A
215
216
217
216
219
22C
221
222
2 2 3
224
225
226
227
228
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231
232
233
234
235
236
237
238
239
24C
241
242
243
244
245
246
247
248
249
25C
251
252
DNUM={TH(I~1 )+TH( I) )/2.-l,
STHOTd J^ST1IH■D^U^*STS^ )
FBU ) = 0,5*(F0(I)+F (in
ETA( n=STS { I )/STC0L (I)
C CQMPtTE STANTON NUf'EGR RATIC FOR TH=1 (IF L = 2 USE FLAT PLATE
C EXPERIMENTAL OATAJ
IF tL,EQ,2 J GG TC 374
STN08( I ) = -0295*PR*4<~.4)^(RElin n**(-.2)
IF (L.EO.l JSTNOBd ) =STNOB ( I !♦ ( 1 •- (XV 1/ ( X ( I l-XVO ) )♦*( 0.9 ) )**
K-U/9.)
374 STHR(I) = STHOT(n/STNOB(n
C COMPUTE STANTON NUPCER RATIO FOR TH=0 (IF L»0 USE FLAT PLATE
C EXPERIMENTAL DATA I
IF (L.EG.2> GO TO 375
STNOB( I )=STN06(I )*(BeX(I l/REXO( II)^*(0.2J
IF (L.EQ.l JSTNOB ( n=STAGP { I M d <XVl*FACTO/REXO( I ))**( 0- 9) »♦*
K-1./9. )
375 STCRdJ-STCOLUJ/STNOBd)
STSR d ) =STHOT( n /STCCL d »
BHCDL( n=FO( I J/STCGU I )
BHOTd )=FC n/STHCTd)
STSFd J=ALOG( l. + BHCT( I )) /BHOTd)
C CORRECT STANTON NUMBER RATIO FOR TH=1 TO COMPARABLE TRANSPIRATION
C CASE USING ALCG( l.-*E) /e EXPRESSION
STHRE(I)=STHRd)/STSF( I)
STSRd ) =SrSRd )/STSF( I )
SF( I)=F d )*STHOT(I )
SFOdJ =F0( n*STC OLd)
362 CONTINUE
DO 363 I=13t36
STSd) = (STO( I )-ST( D) / (THAV-THA VO)
STCOL( I )=STO d)+;THAVO*STS( I )
STHOT( I > = STd )♦( TH A V-1.0)*$TS( I )
ETA( n=STS( I )/STCOLd )
C COMPUTE STANTON NUMBER RATIC FCR RECOVERY REGION, TF = 1
IF (L .EQ.2 ) GO TO 372
STNOBd )=.0 29 5+PR**(-.4)*«REX(I n**<-.2)
IF (L.EQ.l )STNOBd ) =STNOB d ) << 1 .- ( XV I /( X ( I »->Val )♦♦( 0.9) )*★
K-1./9. )
2 72 STHRd ) = STHOTd) /STNOBd)
C COMPUTE STANTCN NUMBER RATIO FOR RECOVERY REGION, TH=0
IF (L.EC.2) GO TO 373
STNOBd )=STNOB(L)*(REXd ) /R E »0 ( I ) )★» ( 0. 2 )
IF (L.EO.l )ST NOB ( I ) =ST NCB ( I 1 4 ( 1 (XV I’^FA CT 0/RE XOd ))>»*(0. 9) )*♦
K-1,/9. )
373 SrCRd )=STCOLd) /STNOBd)
STSRd )=STHOT(IJ /STCCLd )
363 CONTINUE
C COMPUTE 0EL2 AND RECEL2 EASED ON ST-DATA AT TH=0 AND TH= 1
STCOL( 1)=ST0( 1)
STHCTd )=STd)
STS( l)=STO(l)-STd)
DO 370 1=1,12
FHd ) = F( I)
370 TH( I )=1 .0
CALL ENTHAL ( FACT ,SThOT, RENHET, END2 )
DO 450 1=1,12
Fd) = FQ( I)
THd ) = 0.
450 DTH( I)=DTHOC I )
212
c
253
254
255
256
251
25E
259
26 0
261
262
26 3
264
26 5
26 6
26 7
266
26S
27C
271
27 2
273
274
275
276
27 7
278
279
280
281
282
283
284
235
286
287
286
239
OF*OFO
DO 460 I=lt36
460 OST( I)*DSTC(I)
CALL ENTHAL ( FACTO, STC CL fRENCOL ,END2 >
IF (IPRINT.NE.ll GC TO 462
WRITE <6,900)
WRITE (6,40) (NRNOm, 1 = 1,4)
WRITE (6,610) (KCHMC(I), 1=1,40)
WRITE (6,40) (NRN(I), 1 = 1,4)
WRITE (6,610) ^KOMM^T(I), 1=1,40)
462 WRITE (6,371) (NRNO(I), I -1 , 4) , ( NRN ( I ), 1=1,4)
371 FORMAT (lOX, •LINEAR SUPERPOSITION IS APPLIED TO STANION NUMBER*,
I* DATA FROM* / lOX ,* RUN AUFBERS • ,4A2, * AND *,4A2, • TO OBTAIN*
2,* STANTON NUMBER C7TA AT TH=0 AND TH=1'/)
WRITE(6,364I
364 FORMAT ( /,7X, • PL ATE* ,3 X, • REXC CL* , 4X, • RE DEL2 • ,2X ,*ST (TH-0 )* ,4X,
1‘REXHOT* ,4X, *RE DEL2*, 3X , * ST ITH = 1 )* ,4 X, * E TA • ,4X , *STCR* ,4X*F-C0L* ,
25X*5THR* ,4X.*F-H0T* ,4X,*L0GB* /)
WRITE (6, 365) (I.,REXO( I) ,RENCaL(I ),STCOL (I ) ,REX(I) ,RENHOT(I ),
ISTFOTl I) ,ETA( I),.STCf(I ),FC(I ),STHR< I),FH( I ) , ST HR E ( I ) , I =1 , 12 )
365 FORMAT! (lOX, 1 2,2 ( 2XF5 . 1 ) , IXF S. 6, 2 ( 2 XF9. 1 ) , 1XF9. 6 ,2 ( 2 XF5 .3 ) , 2 XF7 *4 ,
12XF7,3,2XF7*4,F8 .3) )
WRITE! 6,36 6) (I ,RE X0( I ) ,RENCOL(I ) ,STCOL( I ) , RE X ( I ) , PENHDT (I ) ,
1STH0T(I),ETA( I) ,STCP( I ) , STHR ( I) , 1 = 13 , 36)
3 66 FORMAT! ( lOX, I 2, 2 ( 2X F 9, I ) ,1 XF 9-6 , 2 (2 XF9. 1 ) , 1XF9 .6 ,2 ( 2XF5.3 ) , 11XF7.3
1 ) )
IF (L.EQ.O) WRITE (6,5C5)
505 FORMAT ( / / , 1 OX, • ST A ^TON NUMBER RATIO BASED CK S T*PR*40 .4=0. 0295*RE
1X**(«.2 ) * )
IF (L.EO -X ) WRITE ( 6, 510)
510 FORMAT (// ,10X ,* ST AAT ON NUMBER RATIO BASED ON ST*PR**0 .4= C. C295*Rc
lX**(-.2 ) •<1.-' ( Xl/( X-XVQ) I*^0i9 )**<-l./9. ) •)
IF (L.EC.2J WRITE (6,515)
515 FORMAT (//, lOX ,* ST ANTON NUMBER RATIO BASED ON EXPERIMENTAL FLAT PL
lATE VALUE AT SAME X LOCATION*)
WRITE ( 6,520)
520 FORMAT (//, lOX ,» ST ANTON NUMBER RATIO FOR TH=1 IS CONVERTED TC CCMP
lARABLE TRANSPIRAYICN VALLE »/10X, 'USING ALCGd ♦ BJ/B EXPRESSION I
2N THE BLOWN SECTION*)
IF ( IPPINT.EC.O) WRITE (6,900)
GO TC 5
2000 WRITE (6,900)
900 FORMAT (IHl)
RETURN
END
FUNCTICN TC(T)
C FUNCTION CONVERTS TEMP FRCM I RON-CONSTANT AN MV TO C£G F
TM=-222 0.7 03 4-781.25*S0RT(7.950782+0.256*7)
TC=TM+49 .97-1.26E-C3*TM-.32E-044TM*TM
RETURN
END
213
29Q
SUBRCUTINE TUNNEL
291
292
29 3
294
295
2S6
29 1
29 6
299
30 C
301
332
303
30^
305
306
30 7
308
309
310
311
312
313
3M
31 5
316
317
218
319
32C
321
32 2
323
32^
325
326
327
328
329
530
.331
3 3 2
C
C
c
c
c
c
c
c
c
c
c
c
c
c
THIS POLTINE COMPUTES THE WIND TUNNEL FLOh CONCITIONS
UINF FREE STREAM VELCCITY (FT/SEC)
TINF FREE STREAM STATIC TEMPERATURE tOEG FI
RHQG FREE STREAM DENSITY IL BM/FT 2)
Vise FREE STREAM KINEMATIC VISCOSITY CFT2/SECI
CP FREE STREAM SPECIFIC HEAT <BTU/LBM/DEG Rl
PR FREE STREAM PRAKDTL NUMBER
W FREE stream ABSOLUTE HUMIDITY ILBM H20/LBM DRY AIR!
COMMON/ BLKl /PA MB i PSTAT t TREOOV , RHUM »POY N
COMMCN/ BLK2 /UI NF ,TI NF,TA D lAB , PHOGt VI SC» PR , CP , W
SATURATION DATA FRCM K AND K 1969 STEAM TABL
DIMENSION TEMPIIO) |PS AT ( 10 I , PH CSAT U 0)
DATA TEMP/
1 90. Of
DATA PSAT/
1 100.627f
DATA RHOSAT/
40. »
1 00. Cf
17.519,
136. E43 ,
50.0 f
110. a,
25.636,
163*787,
60. 0,
120 . 0 ,
36.907,
244.008 ,
.0004090, .00C5868, .0008286,
-0021381, .0026571, .0037722, .0049261,
ES
70. 0, 80.0,
130.0/
52.301, 73.051,
320.400/
-0011525, .0015603
. 0063625/
,
REAL NU,MFA,MFV,MWA ,MWV, JF
TAMBs=TR£COV
DO 1C N=l,9
I FITEMPINI -GT.7AMB ) GO TC 20
10 CONTINUE
20 T = TEMPIN)
EPS = T - TAMB
VAPH = PSATIN)
VAPL = PS/T(N-1)
VEPS = VAPH - VAPL
RHCH = RHQSATIN)
RHOL = RHCSAT(N-ll
REPS = RHQH - RHOL
RHCG = PHOL (10.0 - EPS I EPS / 1 0.
RA = 1545. 32/2 6. S7C
PG = VAPL + (10.0 - EPSI*VEPS/1C.0
PUNlTS=2ll6*2l/33.922/12.
P=PAMBT2116*21/29.9213 ♦ PSTAT*PUNITS
RHUM=RHLM/100-
PVAP = RH'JM*PG
PA = P - PVAP
PHOA = PA/(RA*(TAMB + 459.6711
RHCV = PHUM^RHOG
W=RHOV/RHOA
RHCM = RhOA *■ RHOV
MWA = 28.970
MWV - 18.316
MFV = RHOV/RHOM
MFA = 1.0 - MFV
RM = 1545.32*(MFA/MWA + MFV/MWVI
CP = MFA*3.240 + MFV*0-445
GC=32.1739
JF=778-26
RCF=0.7*^0. 33333
RECOVERY FACTOR FOR WIRE NORMAL TO FLOW
RTC=0.68
RHCG=( P/RM*^PDYN*PUN ITS*RCF/ ( CP*JF ) I / (TRE CO V+-459. 6 7 I
211 ]
333
334
335
336
337
338
339
343
341
34 2
343
34.4
34 5
34 6
347
348
349
350
351
352
353
354
355
356
357
353
35 9
36 J
361
362
36 3
364
36 5
366
367
366
36 9
37C
371
372
373
UINF=SQPT(2i*GC*PDYNl'PUN ITS/RHOGI
T INF=TRFCOV-RTC*UlNf*UINF/<2.4GC*JF*CP )
VI SC= < 1 l.+O* 0 1 7 5*T I ^F ) /( I . E C6*PHOGI * ( 1. - . 7«* W I
PR = .7i0*(530./(TINF>459.67) )**{ .1)>M1.+.
C NOTE FOR HIGH VELOCITY THIS FOUTINE SHOULD EF ITERATED
C CCNVERT TO AEIABATIC hALL TEMPERATURE
RCF=PR*+0. 33333
T ADIAB=TINF+RCF+UINF*LINF/( 2.*GC*JF*CP»
RETURN
END
SUBROUTINE FLOW (KERROP)
C
C THIS ROUTINE COMPUTES SECENDARY AIR FLOW PATES
C
C SAFRU) SECONCARY AIR FLOW RATE CORPECTEC FOR TEMPERATURE
C AND HUMIOIY ICFMJ
C
COMMON/ BLKl /PAMBtPSTAT ,TRECOV,RHUM,FDYN
COMMON/ BLK2 /UlNF ,T INF.TAOIAB , RHOG . VISC .PR ,CP ,W
CQHMCN/ BLK3 /SAFR ( 12 » ,C ! ( 12 T, SK (12 I ,F ( 1 2 1 , KR , Ah ,THE AT
COMMON/ BLK4 /TO (45 J , T 16 ( 12 ) .T 2( 12 ) ,TCA ST( 12 > . TCA V ( 12) ,TH ( 1 2 1
OIMEN.SION X(5) ,Y (5) ,B( 4) .FMC (12) fTM(12)
DATA FMC/ 1.0, 1.22, .92, .988, .928, .9C6, .907, 1.01,
1 .918, .90 1, .920, .929/
C CALIBRATION CURVE DATA
DATA X,Y /0.35, 0.90, 1.12, 1.35, 1.5,
1 53. C, 4.05, 2.00, 1.00, 0.69/
KEPRCR=0
DO 1C 1=1,4
10 B( n=ALCG(Ym/Y (1+1) ) /ALOCOK I)/X( I + l»)
FACT=1.0+0.22*W
DO 20 1=2,12
IF (SAFRd )*EC.O.) GO TO 20
C TM IS ESTIMATE OF SECCADARY AIR TEMPERATURE AT FLGWPE7ER STATION
TM(I )=.5’*(Ti6 (I) +THEAT )
SAFR ( I )=SAFR ( I )*( ( ( TM ( I) +459 *67 ) /530 . )** 0- 7 ) ACT* (3 0. 00/ Cl ( I) ) **?
1 »FMC( I)
2C CONTINUE
FACT=1 .0+0.7*W
DO 40 1=2,12
IF (SAFRd ).EO.O. ) GO TO 40
IF (SAFRU )..LT.X( 1 ) .GR.SAFR4 I),GT.X(5)) GO TC 100
DO 30 K= 1, 5
IF (X(K).GT. SAFRd M GO TO 35
30 CONTINUE
35 Z=Y( K-1 )♦( SAFRd)/ X(K-l) )**B(K-1)
SAFR(I)=Z/(( 530. /(TP(I )+459.67) )^*0 .76 ) / F ACT
40 CONTINUE
C NOTE UNCERTAINTY CALCULATICN FOR FLOWRATE COMPUTED IN
C SUBROUTINE T2EF=
RETURN
ICC WRITE (6,200) SAFR( I)
200 FORMAT ( lOX , • FLOWME TE R READING OUT OF RANGE, E PF=» E12. 5 , //lOX,
1 'DATA SET RECUCTICN TERMNATEO*)
KERR0R=2
RETURN
END
215
suafiou'ffNE raeFF iCFLOwf
THU CO^^UTES
KFU I )
Kt.CNVU »
T'M»
OF-OWdJ
7 M n
'if III i
rU )
XPEF.F MEN' /.t CfiNOU^TAN^r FOft CCFPU'ING f/FLO’l
FH i FEN I it COhDUCTM'CE FCR Cf/'PU iNG i i 6 F -
^ ^FECriVF SECCNCAf.V A? F. T'ifiPER VfUR c
FNE'^.C.Y tCifS f'fiCP ■>LAT i TO 5 ECCNCAPY A IP
/ao; R atj'c ! 4 py up
MAS ' FU-> R/J 10, SEC3 MDAPY A! P TC MftU-STR UM, HHER .
P^rr^iAH/ (f'*P t
rnw^^CN/ BLKl /fAM 8 ,F 5 TA^ ,TRe'X}V,ftHUM,>OVA
CCMMON/ Blf^/ ^ AH HEAT
C if'MCN ' BUi'l /SURi 151 <C I( 1/ l»SfJ 12 ' . ! „ , ^ ^ . tij/12»
CJ-MCN/ BLK 4 /Ta< 4 f>.T;,MU,, 3 |r^
f.T AL KCCN/aZi ,KFL( 12 ) ,Kl»KR,KFF
JiMENilON JFICWI 12 )
HL. = -2 333:2
kr*.:' 333 :*:.
f^BP® # 333333
rwi=TCAS 7 af
TWl 2 ®TC,*'iTl i -M
CAL. CA 2 iTY fKL, KP»K FP ,TLl»Tf)f 2 1
FACr«. 3 ?A 8 ',’*, 2 ^'* 6 C .
QFt.CWi J ®0 .C-
H 0 '.E 9 ® J.
H 0 lE 8 - 8 .
OC X 6 T * 2 ' J .2 ,2
Kf,ONV. I )=').
K'UD^O,
JF c 5 dFRf I 0 . I GO iO 16
If 33 TJ 8
A.OIl H 0 I.E'- 4 .
8 SAFF. J ) = 3 AFR.n )>^‘ 3 ./HOLE '9
IF ( 5 AFRU KGT. 5 , » FO TO 12
KFU n = i . 01 f'’'‘SAF a I 1 i 536 * 30 tt 9
KCOfiVl . 3 ’«S 4 -RnM^‘C. 27 f>'*H 0 Lf 9 /f 0 iCT
GO ro i 6
12 IF ( SAFR U J .GT- ) 0 . J GO 0 l«
Kf I n : 0 . 0 U 0 ^i 4 FR( n»f 0 . 75 CKHCte 9
K; 3 NV(n® 0 . 3 UJ* 5 Af PU **c ,r, 386 -Mfa'jG/FAt.r
14 KFLUf = 0 .'>; 2 *UFR< n** 0 « 5748 *HCl E 9
' 0 :CNVi I l ~ J , 027 ^S AFP n M’f'O ,/, 3 E 6 ^‘ODLf;G/FA . f
“r’w'/eD TO e fOU PCh ISING faCTOP, Hr;'.E 9 ia 5 T£»P D? HOLES
00 3 a 1 = 3 , 12,2
<CCNV( I)= 0 .
KFi.f n*ff .
IF . $AF UI ) . £C* 3 * ) Cl TC 26
SAFU n=SAfP ( I }^ 9 ./H 0 lGfi
IF JSAf F U . GT-f- .) 30 T C 22
K'-L( I > = ;. 0 i 5 *SA=R(I , 3536 >'H 0 U 9
KCCNV( n *0 .0 3 *? A FR f ', I* ‘fu 2733 *H'J'-C 8 / FXCT
c c- TC :.'fc
:>2 pC { s o- R { f i . GT *1 0. 1 CO TO ^4
H':CF 9 ^^STc^O OF HOLES
" •» ^
421
422
42 2
424
425
426
421
42 8
429
43 C
421
43 2
43 3
434
435
436
437
438
43 9
440
441
442
44 3
444
445
446
44 7
44 8
44 9
450
451
452
453
454
455
456
457
458
459
460
46 1
462
46 2
464
46 5
46 6
467
468
469
470
471
47 2
47 3
KFL( IMO-0080*SAFR(I)*40.7501*HaLE9
KCON\(( I )=0-01704S4FRt I )4*0.6388>*‘H0LE8/FACT
GO TO 26
24 KFL( I» = 0.012*SAF R(I J440. 5748*H0LE9
KCCNVU )=0,027*SAFRn ) *40. 43 86 *H0LE8/ FACT
26 CONTINUE
CC EFFECTIVE »T2* ,AN0 'CFLCWi
DO 30 1 = 2 , 12,2
IF (SAFRn)iEO.O'.l GO TO 31
IF ( KM-NE.l) GO TO 33
H0LE9=5,
IF < I.E0.4,GR,I.EU.8.0R.I,EQ112J H0LE9=4.
33 SAFR{ I J = SAFR( n*H0lE9/9.
TEAR=tTOm’*rTCAV( I-l) )*0.5
IF ( I .E0,2 ) 7BAR=T0(I J
IF (I.EQ.2J KCONV( I »=KFt ( I )/FACT
T2(I)=T 16( I) + (TBAR-T16{I ) )*ti.-EXP(-KCQNV( I)/S AFR(1 ) ))
OF LOW ( I )=KFL <1 (TO (Il-T 2< IJ I
GO TO 30
31 T2(I ) = TO(I »
OF LOW( I )=0.
30 CONTINUE
00 40 1=3,12 ,2
IF (SAFR{I liEO.O. ) GO TO 41
SAFRd | = SAFR< n*H0LE3/9.
TBAR=( TOU »TCAV< I-IJ )*0.5
IF ( I.EC.3 ) TBAR = TOH»
T2(n=Tl6(n + (TBAR“T16(I ) ) ♦ ( 1. -EX P {-KCONV ( I)/SAFR(I )))
OFLQWi I )=KFL ( I )* (TC (I l“T 2( 1) I
GO TO 40
41 T21I )=TO(I )
OFLOWC I )=0.
40 CONTINUE
C
C COMPUTE THETA= (T2-TINF)/(T0-TINF)
TH m=o.
DTH( 1 )=0.
C OT : UNCERTAINTY IN TEMPERATURE, F
DT=0.25
C DT2, UNCERTAINTY IN T2, CEG F
DT2=J.5
DO 200 I =2 ,12
TH( I) = ( T2( I )-TINF» / (TO II )-TINF)
C OTH(I); UNCERTAINTY IN TH( I )
2 CO OTH( I i = SQRT(DT2**2+ (THI I )*0T l**2*((l,-TH (I ) ) *01 2 ) / ( TO ( I J-TINF)
C
FACT = Ah/(2.42./144. J
IF (KM.EO.IJ FACT=AH/| 4.44,/144.l
DO 50 1=2,12,2
IF <KM.N£. II GO TO 48
HCLE9=5 .
IF (I.FQ,4.0R, I,EQ.8.OR.I.E0il2I hOLE9=4.
48 F9=AH*60.*UTNF+H0L E9*R HDG
RHOS=RHCG*(TI NF+45 9.67 1/ IT 2 ( II +459.67 I
SMI I ) = SAFR ( 1 )*Rl+09/F9
FI n = SMI D^FACT
50 CONTINUE
F8 = AH*60.=»UINF*HJL E8*RH0G
DO 60 I = 2, 11 ,2
RHCS = RhCG*ITINF*:459.67l/IT2l 11+459.67)
217
<»7 4
475
47 6
47 7
47£
479
480
461
482
483
484
43 f
486
SM{ I ) = SAFR ( I )*RH-nS/F8
F(I)=SM( I)*FACT
C AOJLST F,TH for P/D=10
IF (KH.Eg.lJ F(I )=F(I-1)
IF IKM.FO.l) TH( I)=TH( I-l )
€0 CONTINUE
SM (1 )=0.
F ( 1) =3-
C
c DP ; UNCERTAINTY IN MANOMETER PRESSURE , H20
DP=0.D08
C DSAFR; LJNCFRTAI.NTY in seconeary flow RATEfRATIO
C5AFR=3 .05
C DF: UNCERTAINTY IN F , RAT I C
OF^SORT( D5AFR+0SAF P + OP *DP/ 1 4.<' P CYN* PDYN > )
IF (SM<2). EQ.O.U » CF=0.0
RETURN
END
48 7
C
C
C
488
489
490
491
492
49 2
494
49 5
49 6
497
49 8
499
5CC
501
5 72
503
504
50 5
506
50 7
50 8
509
510
51 1
51 2
512
514
515
516
SUBROUTINE CAVITY I KL , KR , K B P ,TW 1 , Tw 1 2 )
This ROUTINE CONFUTES TEST SECTION CAV ITY T FMPEPA7URES
REAL KL,KH,KBP
COMMON/ BLK4 /TO ( 45 J ,T 16( 12 ) ,T2 ( 12) t TCASTI 12 ) ,TCAV( 12 ) ,TH< 12 )
TCAST2 =TCAST( 2 )
TCAST5=TCAST( 5 )
TCAST8=TCAST ( 8 )
TCAS11 = TCA 57( 11)
D8P1=TCA3T5-TCAST2
DBP2=TCAST8-TCAST5
0SR1=TCAST 16 ) -TC AST (3)
0SR2 = rCAST( 7)-TCASr (4 )
DBPl=TCAST(5)-rCAST(2)
DBP2=TCAST (8) -TC AST (5)
TCAV( 1) =KL*( TCASn 3 )-l ./4.*D'Rl )+KR+ (TCAST (4)- 1 -/4.+DSR2 )
1 +K8P+(TCAST aj*-Twi>
TCAVI 2 ) = KL*TCAST{3 ) ♦-KP’^TC AST (4) +KBP»TCAST2
TC AV13) =KL*1TCA3T( 3 J+-1 ./4.5*CSR1)+KR*(TCA5T( 4) + i./4.5*D SP 2 )
1 +KBP^= (TCAST 2+1. /3 .WB PI )
TCAV (4)=KL+(TCAST(3 ) + 2./4.5*CSR 1 1 +KR » ( TC AS T ( 4 ) +2. /4, 5*03R2)
1 +KBP«'( TCAST2 + 2. /3 . +DB FI )
TCAV (5 ) = KL*( TCASK 3 )+3./4.5*CSRl)+KR*(TCAST(4)+3./4.5*D3R2)
1 +KBP*TCA3T5
TC AV(6 ) =KL>*=( TCAS^( 3 ) + 4 . /4 . 5 ♦CSR 1 ) +K R’(' ( TC AS T ( 4 ) 4 4 . /4 . 5 SR2 )
1 +KBP* ( TCAST5+1. /3 . 4CBP2 )
DSR1=TCAST(9)-TCAST(6)
DSR2=TCA37(10)-TCA3T( 7 J
DBF3=TCA51 1-TCAST8
TC AV(7 )=KL1<( TCAST ( 6 ) +0 .5 /4 . 5 ^DSR 1 ) + KP *( TCA ST ( 7 ) +C « 5/4. 5*DSR2)
1 +KBP4C (TCAST5 + 2. /3 .i'DB F2 )
TCAV (8 ) = KL*( TCA5T( 6 ) + 1.5/4.5^DSRl)+KP*{TCAST(7)+1.5/4.5’^'DSR2 )
1 +KBP+TCA5T8
TCAV(9)=KL*{ TCASTt 6 ) + 2.5/4.5*OSRl) + KP'k(TCAST(7)+2 .5/4.5*nSR2»
1 +KBP+(TCAST8 + l. /3. ♦'DBP3 )
TCAV( 10 )=KL*( TCA ST ( 6) + 3. 5/4- 54< DSR 1 ) + KR* { TC AST ( 7 ) +3 .5 /4 . 5 CS P 2 )
1 +KeP*(TCAST8+2./3 .VD8P3 )
TCAV (11 )=KL*TCAST(9 ) + KR*TCAST( 1 0) +K8P*TC ASH
TCAV (12 ) = KL+ (TCAST ( 6 ) +5 . 5/4 . 5*DSR I ) +KR TC A S T ( 7 ) + 5. 5/4. 5* DSR 2 )
1 +KBPV (TCAST ( 12) +TW12 )
RETURN
END
218
5X7
5 LB
519
520
521
522
535
53£
527
538
539
540
SUBROUTINE POWER ( TIN F«0 FLOW «A I
THIS ROUTINE :
U) CORRECTS TFE INDICATED PLATE POWER READING FOR
WATTMETER CALIBRATION AND CIRCUIT INSERTION LOSSES
(2) COMPUTES NET ENERGY LOST FROM PLATES BY FORCED
CONVECTION HEAT TRANSFER
(3) CCMPUTES HEAT FLWX FROM RECOVERY REGION PLATES
COMMCN/
BLKA /TO
BLK5 /Ql
f45ltT 16(12},T2«12JtTCASTU2}t TCAVf 121 «TH( 12)
COMMON/ BLK5 /Ql 12 > rHH 145) t VARf 12) tOOOT 1 36 )
COMMCN/ BLK6 / OXVO *CEND2 , DF » GREENI36 ) f DSTI 36) t OODOTI 36 1 * DTH ( 12 )
REAL KL*KR,KBP,K
523
DIMENSICN X6(12)
,QFL0W(1 )
,K139I,S(40)
C
CONDUCT IDN LOSS CONSTANTS FOR TEST SECTION
524
DATA K/ .2700t
-.2705,
A1851, .2800, .1781, .2763,
1
.1760f.
.2768,
J1721, .2832, .1806, .2800,
C
HEAT FLUK METER CALIBRATICN CONSTANTS NO 13-36
2
34.00*
35.30,
35.04, 34.04, 33.64, 32.25,
3
24.83f
34.04,
27.55, 31.55, 29.61, 31.80,
4
34.0lf
24.24,
35.75, 29.30, 24.50, 31.46,
5
32 • 06r
39.35,
32.73, 23. 60, 36.27, 33.24,
C
HEAT FLUX METER CALIBRATICN CONSTANTS NO 106-108
£
32.53,-
32.6 2 ,
36i65/
C
AXIAL CCNOUCnCN LOSS
CONSTANTS
525
DATA S/ 1.200 (
11*2.3,
.950 , 6.23, 4.962, 5.014, 4.965,
1
5^118,
5-18 2,
4.777, 4.494, 5.480, 5-020, 5.5?7,
2
5w254,
5.169,
5.254, 5.356, 5.211, 5.370, 5.583,
3
4^990,
5.435,
4.172, 5.557, 5.545, 5.585,
4
4L983,
5.056,
6.34 /
526
DATA
RO
/
8.476,
8.595,
8.500 ,
8. 506,
8.478,
8.571,
1
8. 549,
8.641 ,
8-590,
8. 63 8 ,
8.481 ,
8.504/
527
DATA
RBO
/
8.386,
8.502,
8.426,
8.418,
8.366,
6.471,
1
a. 445,
6- 574,
8.509,
8.528,
8.391,
8-393/
528
DATA
RR
/
0. 0408,
0.054Ii
0.0406,
0. 0411,
0.04X3,
0.0412,
1
0.0410,
0.0415,
0.0409,
0.0409 ,
0.0406,
0.0406/
529
DATA
RLOC/
8.256,
8.331,
8-237,
8. 22 1,
E.239,
8.269,
1
8.227,
8.238,
8.250,
8.253,
8.240,
0.248/
530
CATA
RWAT/
8.400,
8.464,
8. 379 ,
8. 367,
8.4C5,
8.429,
1
8.42 2 ,
0.541,
8.544,
8.412,
8.366,
8.411/
53 1
DATA
RON
/
8.313,
8.387,
8.281,
8.282,
8. 3 16 ,
8.335 ,
1
a. 330,
8.455,
8.451,
8.428,
6.296,
8.291/
53 2
DATA
RL
/
8.077,
8.157,
8.057^
8. 047,
8.067,
8.087*
1
8.037,
8.057,
8.067,
8.C77,
8.057,
8.057/
533
DATA
XB
/
12*0./
534
DATA
RA,
XA
,RV,RVM/
0.064,
0.C63,
75C0-0,
5300.0/
THIS BLOCK CORRECTS INDICATED WATTMETER READING USING
WATTMETER CALIBRATICN ECUAT ICN
DO 10 I»ltI2
QP*OII ) /75,
QCOR-QP* (0.0728* QP-X). 0 42 7*C P*QP-0. 0292)
QCCR»0.99*0U )<-QC0R*75.
THIS BLOCK CORRECTS FOR -WATTMETER INSERTION LOSSES
VARR-RR(1)*VAR ( U
SUMRO-RO (I)*VARR
219
I
541
542
543
544
545
54 £
547
54 C
549
550
551
55 2
553
554
555
556
557
558
5 55
56 ^
561
562
56 3
564
565
566
567
568
569
57.0
571
572
573
574
575
574
57 7
578
579
58C
581
582
58 3
534
585
58 6
587
SU#lRBa*PBO (D+VARR
FP 1*RWAT(I )/RVMfr l.
2ROSQ=»SUMRO*SUMRO«(X8( I I^XA/CPl I* <X Bl D-t-XA/FPl)
ZRB0SQ«SLMR80«SUHRBC>XBi
RVMONS-«RVM/(RVM+RON(IJI >♦ ( RVM/ (.-RVM+ROW I) 11
ZVALSO* |RV^RA+RLOD( II J*(RV+RA*RLOOn ) M-XA4XA
Qm=QCCR*lZROSQ/ZREQSGI*<ZVALSQ/RV/RVl*BVP,CNS
1 *FPl«FP14|RLfI }/n>A4-RL0C<I1l )
10 CONTINUE
C
C THIS BLOCK CORRECTS POWER DELIVERED TO PLATES
C IN TEST SECTION FOR CCNDUOTIGNtRAOI ATION* AND QFLOW LOSSES
SF«1.
EM IS=0.15
TAR»ITINF+460.)/ 100-
TH1*TCAST(1J
TW12*TCAST (12 I
KL»0-5
KR*0-5
KBP>0.0
CALL CAVITY (KL, KR ,KBP .TW1,T«)12 I
TUP»TO (45)
TO OWN- TO (13);
TW1=TO(45H-K((39)*HM(45I/20.5
T«12=T0(13H-K(13 )*HH(13)/20-6
TO(13I=0.75*TO( 13)+0.2f4TW12
TQ(45)=0.75*T0(45) *0. 25*TW1
IF ( HM( 131 -EQ-O. I TC( 131 =0.5*(T0( 121 ♦T0( 13)1
IF (HM(45J -EQ.O. I T0( 45 )*0 . 5«(T0( 1 ) +T0C45 ) )
DO 109 I«ltl2
TOR*(TO( I ) ■*460.1 /I 00.
IF (I. EG. 1) 60 Tb 98
0C0ND=K( 1)>MT0(I )-TCAV(I )) ♦SIII*(TO( I I-TOU-IJ S (U D* (T0( II-
1 T0(I*1I)
GO TO 100
»8 OCOND=K( I)>MTC(I )-TC4V(I ) )*S4II*(T0( I )-T 0(451)
1 ♦$(! *^1)*(T0(I)-T0(I-*1J >
ICO QRAO*A*Sf*EHIS4.1714*(TOR*TOR*TOR*TOR-TAR4TAR*TAR*TAR)
C
C ENERGY BALANCE IS ^PPLIEC TO PLATE
GLOSS«QCONOQRAD*-QFLOW(I )
0(I) = Cm-0LOSS/3.4129
ODOTI I )=0( I )*3. 4129/A
109 CONTINUE
T0(45)=TLP
T0(13)=T00WN
C
C THIS BLOCK COMPUTES HEAT 6LUX FROM RECOVERY REGION PLATES
SF*1.0
EMIS=0. 15
T0(37)=T0(36)-.333*(T0(36)-T0(37II
S(13)»7.0*S(13)
TAR»(TINF+460-)/ 100.-
00 200 1*13,36
TOR*ITOI II+/460.J /I OC-
2 CO QDOTf I) = K(I)*HM(tI)4(l. ♦( 80 .-T0( 1 1 1/700. )
1-S( Il*( T0( I)-T0( I-IJ )-S(I^l)*(TO( I)-TC( !♦! I )
2 -SF*EMIS*il714*(TCR*TCR4TOR*TOR-TAR*TAR*TAR*TAR)
S( 13)=S( 13) /7.0
C
220
sea
58S
59C
591
592
592
594
595
59 ^
591
59 8
59?
600
60 1
602
603
60 ^
60 5
606
6Q7
60 €
60?
61C
611
612
613
614
615
616
617
616
61?
620
621
C ASSlIME ALL PROPERTIES CCPFECT* AFTER TEMPERATURE-HUMIDITY CORRECTIT^.
C DO! ENERGY BALANCE ERRCRt WATT
OQ-0.3
C CHM: uncertainty in
0HM*0*025
C ok: uncertainty in heat flux meter CALIBPATICNt ratio
DK»0.0 3
C DS: UNCERTAINTY IN CONCUCTIC^ CCRRECTION ON HEAT FLUX METER tP AT 10
DS»0.05
C OT: UNCERTAINTY IN TEMPERATUREf F
OT-0.25
C DCDOT: UNCERTAINTY IN HEAT FLUXt 8TL/HR .SOFT
DO 711 I»l,12
711 DOOOTI I)*DQ*3.4129/ A
00 712 I»13^36
712 DQDOU I »=SQRT(0K*0K*K( I)4K( I |4HM( II *HM( I I ( I) *K( I l*DHM*OHM+DT*OT
I4(sui4sn )aS(i«-:i)*s(i«i j l♦DS*os*^s^ i*s n iaitcii )-to(i-ij mitoc ii
2-T0(I-in*S( I+1)*S( 1+11*1 TOU)-TO( I ♦!) I* <T0( II-TCCI+l) ) M
RETURN
END
SUBROUTINE ENTHA L ( FAC T. ST, REEN,EN02I
C
C COMPUTE ENTHALPY THICKNESS, ASSUMING THERMAL BL BEGINS AT
C LEADING EDGE OF PLATE 1. COMPUTATION BASED GN CONTROL
C VOLUME FOR ENERGY ACDITIQN WITH BCUNDPIES PLATE CENTER
C TO PLATE CENTER! EXCEPT PLATE 1)
C
COMMON/ BLK3 /SAF R ( 12 I ♦ C I <121 ,SM* 12 I ,FU 2 > , K F , AH, THE AT
CCMMCN/ ELK4 /TO < 45 ) ,T 16( 12 KT2 <121 , TCASTI 121 , TCAVI 12 ) *THC12 )
COMMCN/ BLK6 /OX VO , CEN C2 , C F , GREEN (36 I ,OST ( 36 I , CCCCT ( 36 I , OTH ( 12 1
OIMENSICN STUI, REENin, C2 f 31) , 002( 3 6 )
TH(l)=0.0
DTHIl ) = 0.
FU I *0.0
DX=l.
DWX*. 515625
C DDX: UNCERTAINTY IN DX, IN
DDX»0.005
D2(l )*EN02
002( 1)=0END2
IF (ENC2-E0-0.I D2(l )=ST(1)*0X
IF< .N0T.END2.EQ.0. > GOTO 229
C 002(1); UNCERTAINTY IN ENTHALPY THICKNESS, D2, IN
DD2( 1)=S0RT(0X*DX*CST( 1)*DSTU )+ST(l )*ST(1 )*CCX*DCXI
229 DO 230 1=2,12
D2U ) = D2(I-1) + (ST(I-1)+ST(I ) t2 . *F (I -1 )*T H( I-ll )*0X
AL=ST( I l*ST<I J+ST<I-l)*ST( I-l) +F ( I )*F ( 1 1 *TH( 1) *THU ) +F( I- II *
1F( I-1)*TH( I-l l*TH< I-l )
BE=DST( I l*OST( I) +OST( I-l )*DS1( I-l)+f (I)»F( II*DTH 1 )*DTH( I 1 +
1F( I-l )*DTht I-l )*CTM I-1)+0F*DF*<F<I l*F( M*TH< I)*TH( I )+
2F( I-l)*F(I-l)*TH(I-l)*TH(I-ll)
230 DD2(I)=SQRT(CC2( I-U*DC2( I-l 1+D0X*DDX*AL+DX*CX*BE 1
02( 13)=D2< 12) + (ST( 1 2 ) + 2.*F ( 12)*TH ( 12 I )*0 X+ST (1 3 )*CWX
DD2( 13»=SQRTCD02 (12 )*DC2 ( 12 ) ♦DDX*DDX*(ST C I 2) *ST< 12) + ST( 13|*ST(13)
1+F(12)*F(12)*TH( 12)*TH(12) I +OWX*CWX*CST C 1 3)*0ST < 13 ) + 0X*0X*C
20ST( 12I*DST<12H-F( 12)*F( 12I*CTH( 12)*DTH( 12 )>CF*OF*F( 12 )*F(12I*
2TH(12)*TH(12)I)
221
I
62 2
623
624
625
626
62 7
62£
62 5
63C
DO 231 1=14, 26
D2(I J = D2(I-1 ) + (STn-l)*ST< III*DWX
IF I I.EQ.14iAND. KM. EO. i) C2 U4) =D2 ( 14) *2. *F ( 1 2 >*TH < 12 ) *DX
221 D02II)= iQRT(CC2( I-U*DD2i I- i ) + DDX*DDX* ( ST ( I >*5T( I)+ST(I-U#
IST(I-l) )♦ DWX*DWX*(CST(I)*CSTm+DST<I-l )*DSTU-in)
C COMPUTE ENTHALPy THICKNESS REYNOLDS NUMBER FGR CENTER
C OF PLATE BASED C^ D2( I) FER ENERGY ADDED TO ThAT POINT
DO 240 1=1,36
RtENd )=PACT*D2( I)
240 DREENCI )=FACT*DD2( I)
RETURN
END
222
Appendix- IV
ON THE HEAT TRANSFER BEHAVIOR
FOR THE INITIAL FILM-COOLING ROWS ;■
Consider, for example, the data for 0=1 and M = 0.4 in Figure
3.3 or the data for M = 0.2 and 0.4 in Figure 3.6. It can be seen
that introducing hot fluid onto a hot wall (6 = 1) causes Stanton num-
ber reductions of about 10 and 30 percent for the first two rows of holes,
respectively.
The identical Stanton number reduction for M = 0.2 and 0.4 with
6=1 indicates a similar hydrodynamic behavior for the initial blowing
rows and low M. (In fact, this type of behavior is seen for low M in
all the p/d = 5 data.) Presumably, for low blowing ratios the jets are
immediately knocked over onto the surface by pressure forces. The Stan-
ton number reduction for low blowing ratios can be explained by consider-
ing the folloy/ing simple analysis, along with the sketch below.
223
As the jet of coolant emerges from a hole in the first row, it will
displace the boundary layer fluid and the new fluid will lie along the
surface downstream. The total heat transfer from the surface (for an
area associated with one hole) can be decomposed into two parts,.
q
“Iconv + •12
(IV. 1)
Introducing a convective rate equation, the heat transfer rate becomes
q = h A (T -T J + h^ A.(T -T.) (IV. 2)
conv conv o«» 22 o2
where the subscript ''2” refers to the injectant conditions.
By forming a Stanton number, equation (IV. 2) becomes
(IV. 3)
where A = (A + A„) and 0 is the temperature parameter. Thus,
conv L
= S^conv • ^ r
For the first blowing row, in the limit as M 0, h« ^ h ;
2 conv
for larger M, h„ > h . Consider the limiting case for P/D = 5
2 conv
and 0=1.
St(0 =0) = St
o
(IV. 5a)
St(0 = 1)
St
o
A
conv
0.90 St
o
(IV. 5b)
where St^ is the Stanton number at M = 0. This 10 percent depression
is precisely the Stanton number behavior for Figure 3.6 for no upstream
thermal boundary layer. Note that the corresponding prediction for
0=0 is St(0 = 0) = St . The fact that St(0 = 0) > St for Figure
o o
224
3.3 reflects the influence of the existing thermal boundary layer.
However, the St(0 = 1) behavior is identical to that in Figure 3,6.
If the same analysis and assumptions are carried out for the second
row of holes, it is found that
St(0 = 1) = 0.70 St^ (IV. 6)
which' is precisely what the experimental data exhibit in Figures 3,3
and 3.6.
To proceed further would be meaningless because of the fast growth
of the thermal boundary layer and Increased turbulent mixing. The analy-
sis is Intended only to explain the data trend for the first two rows of
holes.
225
Appendix V
ON AN ASYMPTOTIC STANTON NUMBER AND JET COALESCENCE
It Is perhaps important to readdress the 6=1 data and ask
whether it will approach a constant, non-zero value or whether it will
monotonically continue to decrease. Recall that most of the 6=0
data approaches an asymptote, independent of the number of rows of holes.
The importance of the question is embodied in a relation derived by Choe
et al. (1976) to relate the Stanford data to effectiveness data.
_ St(M,0=l)
St(M,0=O)
(V.l)
Consideration of this equation is made in light of the r\ data of
Metzger et al. (1973) and Mayle and Camarata (1975). Note that the only
ways for ri to approach a constant is for St (6 = 1) and St(0 = 0) to
decrease at the same rate, or for St(0 = 1) to approach a constant in
a manner similar to the St(0 = 0) data of Figure 3.3.
Metzger’s data at M = 0.2 (normal-angle injection) showed a near-
zero derivative in rj at about 40 hole diameters downstream. Mayle and
Camarata found that for M = 0.5 (compound- angle injection) the deriva-
tive dr)/dx becomes zero (100 hole diameters downstream of the array
leading edge) for all P/D. Mayle and Camarata write, in explanation:
"This result indicates a balance is nearly reached between
the jet-mainstream mixing, which reduces the cooling effect,
and the periodic coolant injection which, of course, is intended
to increase cooling. At higher mass flux ratios the film effec-
tiveness is seen to be still increasing at the last row of holes
[writer's note: 25 rows of holes for their P/D = 8 surface];
however, the rate of increase is reduced from that of the first
half of the pattern. Besides being a consequence of the film
approaching the coolant temperature, with the result that each
successive injection is less effective when based on the original
coolant-mainstream temperature difference, the reduced rate of
increase is also a consequence of jet coalescence."
In support of a constant effectiveness, the study by Choe (the nor-
mal injection study at Stanford that preceded this study) did obtain
data with near-constant effectiveness for M = 0.2. However, for these
226
data both St (6 = 0) and St (6 = 1) were decreasing at the same rate
to produce this constant r| condition.
The data reported herein for 30-degree slant-angle injection show
no evidence of producing a constant effectiveness, as would be calcula-
ted according to equation (3.1). Note that ri is calculated for all
data sets and is given as a part of the tabulations in Appendix I. How-
ever, based on the Mayle work, it is probable that the 55 hole diameter
flow length of the P/B = 5 Stanford test section is not long enough
for establishment of a constant Stanton number with slant-angle injec-
tion at low M and 0=1. It is interesting to note that the film-
cooling model, discussed in Chapter 4, predicts that St(0 = 1)
approaches a nearly constant value when the computations are carried out
for 24 rows of holes.
The question of jet coalescence with full-coverage film cooling
(mentioned in the preceding quote by Mayle and Camarata) was first raised
to us in a private communication with Prof. J. H. Whitelaw, Imperial Col-
lege, London. If the jets begin to coalesce, the cooling will be reduced,
as Mayle and Camarata indicate, because the area of coverage will be re-
duced. This could contribute to an as 3 nnptotic Stanton number behavior.
Following Whitelaw’ s suggestion, a check for coalescence downstream of
the last blowing row of the slant-angle test section was carried out by
S. Yavuzkurt , a research student in the Mechanical Engineering Department
at Stanford. He probed the velocity and thermal boundary layers for in-
jectant conditions at high blowing ratios (up to M = 2.0) and found no
evidence of jet coalescence.
227
Appendix VI
SHEAR STRESS AND MIXING-LENGTH PROFILES
The shear stress profile is computed following a procedure given in
Simpson, Whitten, and Moffat (1970). The shear stress in the bqundai^
layer over a film-cooled surface can be written as.
T-T
O
P
^00 CO
d6
2
dx
P u
^00 00
_eiL
PooUco
dy
m. /A
+
P<xUeo
(VI. 1)
U -
U- cos a\
2 _ \
U /
00 /
In the above equation, the mass flux into the boundary layer is pre-
sumed to have a velocity component U^. Integration of equation (VI. 1)
to y = 6 results in the momentum integral equation of the form given
by Choe et al. (1976) .
m. /A
-Jg-t _
P^U_
II 2 cos a \
u )
00 /
(VI. 2)
Combining the above two equations, the following equation can be ob-
tained :
1 +
F
(1
- M cos
a)
t'*' = 1 +
Cj/2
^2
’ J
r
0 p U
'^OO <
u
pu
dy
. F
r
u
^ TUf
cos a
■
Jo
P u
*^0O 00
^ C,/2
>
M
where = t/t^, C
=
= T /p
0 ^00 00
, and
F
and
M are
dy
(VI. 3)
ter 1.
Equation (VI. 3) is the computing equation for T . From this the
mixing- length can be computed. The shear stress is defined as
_T
P
(V
3y
(VI. 4)
228
I
where is the eddy diffusivity for momentum. It can be defined in
terms of the Prandtl mixing-length as
'M
- Z'
3y
(VI. 5)
Combining the above two equations results in the computing equation for
the mixing-length profile.
p c
^00 oo J
to
1
au
ay
9y
The key to computing the shear stress and mixing-length profiles is
an assumption for C^/2. This was obtained using the value for
the spanwise- aver aged profile and an analogy between (Cf/Cf^) and
(St/St^). For the evaluation of the equations, = 0.001 was used.
The value of the friction coefficient is relatively unimportant; what
is important is the qualitative trend of and Z for the spanwise-
averaged profile.
229
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231
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